E Weapons Delivery Manual"

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T.O. 1F-4C-34-1-1

This manual is incomplete without T.0.1F 4C—34— 1—1 — 1, T.0.1 F—4C—34—1—1—2
and is augmented byT.0.1F-4C-34-1-2.

Commanders are responsible for bringing this manual to the attenuation of all affected
personnel.

Published under authority of the Secretary of the Air Force.

AIR FORCE - 16 February 1973 - 3100

4C —34-1-1-0)

15 MARCH 1970

CHANGE 9-26 JANUARY 1973

AIRCREW WEAPONS DELIVERY MANUAL
(NON-NUCLEAR)

USAF SERIES F-4C, F-4D
AND F-4E AIRCRAFT

MCDONNELL AIRCRAFT
NOw( A >63-0032-i
N00019-71 -C-0213

T.O. 1F-4C-34-1-1

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T.O. 1F-4C-34-1-1

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Q. ■

T.O. 1F-4C-34-1-1

TABLE Of CONTENTS

Section

Page

Section

Page

Introduction.

Supplementary Data.

. . 4-1

Safety and Operational Supplement

Planning Procedures and Sample

Summary.

Problems.

. • 5-1

Time Compliance Directives....

Planning Charts and Tables . .

. . 6-1

Description.

i-i

Glossary.

Glossary 1

Normal Aircrew Procedures. . . .

2-1

References.

Reference 1

Emergency Aircrew Procedures . .

3-1

Alphabetical Index.

. . Index 1

INTRODUCTION

SCOPE

This manual contains data to plan and execute an air-
to-ground or air-to-air combat attack and/or train¬
ing mission using the F-4C, F-4D, and F-4E air¬
craft and the non-nuclear weapons. Weapons delivery
techniques or tactics are not included except to de¬
scribe a particular delivery mode or maneuver, or
to support certain ballistic data. For Tactical
Fighter Weapons Employment procedures and tactics,
refer to Air Force Manual 3-1 (Secret Noforn). The
following non-nuclear weapons and associated train¬
ing equipment are included in this manual.

A/A 37U-15 Tow Target System (Modified)

A/B 45Y-1 Spray Tank
A/B 45Y-2 Spray Tank
A/B 45Y-4 Spray Tank

AGM-12B (Bullpup) Missile (formerly GAM 83)

AGM-12C/E (Bullpup) Missile
AIM-4D Training Missile
BDU-33/B (Formerly MK 76) Practice Bomb
BDU-33A/B, B/B Practice Bomb
BLU-l/B, B/B, C/B Fire Bomb, 750-lb
BLU-27/B, A/B Fire Bomb, 750-lb
BLU-52/B, A/B Chemical Bombs
BLU-76/B GP Bomb
CBU-lA/A Dispenser and Bomb
CBU-2/A, A/A, B/A, C/A Dispenser and Bomb
CBU-7A/A Dispenser and Bomb
CBU-9/A, A/A, B/A Dispenser and Practice
Bomb

CBU-12/A, A/A Dispenser and Smoke Bomb

CBU-24/B, A/B, B/B, C/B Dispenser and Bomb

CBU-29/B, A/B, B/B, C/B Dispenser and Bomb

CBU-30/A Dispenser and Bomb

CBU-33/A Dispenser and Mine

CBU-34/A, A/A Dispenser and Mine

CBU-38/A, A/A Dispenser and Bomb

CBU-42/A Dispenser and Mine

CBU-46/A Dispenser and Bomb

CBU-49/B, A/B, B/B, C/B Dispenser and Bomb

CBU-52A/B, 52B/B Dispenser and Bomb

CBU-58/B Dispenser and Bomb

CBU-70/B Dispenser and Bomb

CBU-71/B Dispenser and Bomb

Combat Documentation Cameras

CTU-1A Resupply Container

Laser Guided Bombs (MK 82, MK 84, M-118)

LAU-3/A Rocket Launcher, 19-2.75-inch FFAR

LAU-32 Rocket Launcher, 7-2.75-inch FFAR

LAU-59/A Rocket Launcher, 7-2.75-inch FFAR

LAU-68A/A Rocket Launcher, 7-2.75-inch FFAR

LUU-l/B, -5/B, -6/B Target Marker

LUU-2/B Flare

MC-1 Gas Bomb, 750-lb

MK 20 Mod 2 and Mod 3 Cluster Bomb (Rockeye n)

MK 24 Flare

MK 36 Destructor

MK 82 GP Bomb (Snakeye), 500-lb

MK 82 LDGP Bomb, 500-lb

MK 83 LDGP Bomb, 1000-lb

MK 84 LDGP Bomb, 2000-lb

MK 106 Practice Bomb, 5-lb

MLU-32/B99 Flare (Brighteye)

M36E2 Cluster Incendiary

Change 8

T.O. 1F-4C-34-1-1

Ml 17 GP Bomb, 750-lb

Ml 17 (Retarded) GP Bomb, 750-lb

Ml 17D Destructor (Retarded), 750-lb

Ml 18 GP Bomb, 3000-lb

M129E1, £2 Leaflet Bomb, 750-lb

PAU-7/A Spray Tank

Radar Scope Camera

RMU 8/A Reel Launcher

SUU-7A/A, B/A, C/A Dispensers

SUU-13/A, A/A Dispensers

SUU-16/A and SUU-23/A Gun Pods, M61A1 Gun

SUU-20/A, A/A, B/A Bomb and Rocket Dispenser

SUU-21/A, Practice Bomb Dispenser

SUU-25A/A, B/A, C/A Flare Dispenser

SUU-30/B, A/B, B/B, C/B Dispensers

SUU-36/A Dispenser

SUU-38/A Dispenser

SUU-42/A Flare Dispenser

TDU-ll/B Target Rocket (5-inch HVAR)

TDU-22A/B Tow Target

TMU-28/B Spray Tank

Umbilical Test Set (UTS) AN/AWM-19

2.75-in. FFAR (Rocket)

20mm ammunition

ASSOCIATED NONNUCLEAR WEAPON DELIVERY
MANUALS

I T.O. 1F-4C-34-1-1-1

(FORMERLY T.O. 1F-4C-34-1-1A)

See T.O. 1F-4C-34-1-1-1 (Confidential) for descrip¬
tive and procedural data pertaining to the following
associated with F-4C, F-4D thru Blk 33, and F-4E:

AGM-45 (Shrike) Missile.

AIM-4D (Falcon) Missile.

AIM-7D (Sparrow HI) Missile.

AIM-7E (Sparrow HI) Missile.

AIM-7E-2 (Sparrow in) Missile.

AIM-9B (Sidewinder) Missile.

AIM-9E (Sidewinder) Missile.

ECM Pods.

F-4C/D/E Fire Control System.

Laser (IR) Guided Weapons.

| Pave Knife Pod.

Radar Homing and Warning System (RHAW)

TISEO (Target Identification System, Electro-
Optical)

TV (EO) Guided Weapons

I T.O. 1F-4C-34-1-1-2

(FORMERLY T.O. 1F-4C-34-1-1B)

See T.O. 1F-4C-34-1-1-2 (Secret) for descriptive
and procedural data pertaining to some weapons and
equipment associated with F-4C, F-4D thru Block
33, and F-4E aircraft.

T.O. 1F-4C-34-1-1CL-1

See T.O. 1F-4C-34-1-1CL-1 Aircrew Weapons Deliv¬
ery Checklist (Unclassified) for the abbreviated pro¬
cedures contained in the following non-nuclear weapon
delivery manuals:

T.O. 1F-4C-34-1-2

See T.O. 1F-4C-34-1-2 (Unclassified) for the ballistic
tables of the weapons described in T.O. 1F-4C-34-1-1.

T.O. 1F-4C-34-1-2A

See T.O. 1F-4C-34-1-2A (Confidential) for the classi¬
fied ballistic tables of the weapons described in T.O.
1F-4C-34-1-1.

T.O. 1F-4C-34-1-3

See T.O. 1F-4C-34-1-3 (Confidential) for descriptive
and procedural data pertaining to the following weapons
and equipment associated with some F-4D aircraft.

a. SUU-41B/A, -42A/A Dispensers.

b. Loran-D Navigation Equipment.

T.O. 1F-4C-34-1-3CL-1

See T.O. 1F-4C-34-1-3CL-1 (Unclassified) for the
abbreviated procedures contained in T.O. 1F-4C-34-
1-3.

T.O. 1F-4D-2-31

See T.O. 1F-4D-2-31 (Unclassified) for Aircraft
Maintenance, Flight Operations, and Illustrated
Parts Breakdown of the Coin System and Related
Equipment. This manual contains the bombing tables,
mission planning data, and inflight procedures asso¬
ciated with the ADSID-1 Normal, and Long Life
ADSID (TC-425) Coin stores.

EXTERNAL STORES LIMITATIONS

See Flight Manual T.O. 1F-4C-1 (Unclassified) for the
limitations associated with carrying, releasing, and
jettisoning of the non-nuclear weapons. Only the ex¬
ternal stores listed in the Flight Manual may be car¬
ried and released.

Note

Classified External Store Limitations are lo¬
cated in section IV of T.O. 1F-4C-34-1-1-1.

The load configuration of a store having
classified limits is normally unclassified
and repeated in the Flight Manual T.O. 1F-
4C-1.

ARRANGEMENT

Sections I, II, and HI of this manual are divided into
four parts according to aircraft effectivity: Part 1,
F-4C;Part2, F-4D;Part3, F-4E; and Part 4, F-4C/
D/E. This format will permit the user to reduce the
size of the manual by removing the parts or sections
that are not required.

a. T.O. 1F-4C-34-1-1.

b. T.O. 1F-4C-34-1-1-1.

c. T.O. 1F-4C-34-1-1-2.

Change 8

SECTION I, DESCRIPTION. This section contains a
description of the various weapon delivery modes, the

T.O. 1F-4C-34-1-1

■

weapons employed and associated equipment, the
multiple weapons release system, and the aircraft
controls and indicators.

SECTION II, NORMAL AIRCREW PROCEDURES. The
normal aircrew procedures employed in dive bombing;
rocket launch, strafing, loft bombing, and practice
bombing using the SUU-20/A, -20A/A Bomb and
Rocket Dispenser and SUU-21A/A Bomb Dispenser
are contained in this section.

SECTION HI, EMERGENCY AIRCREW PROCEDURES.
This section contains the emergency release proce¬
dures, the jettison procedures, and the fire fighting
and evacuation data. Emergency procedures are
identified by black diagonal stripes at the top corner
of each page.

SECTION IV, SUPPLEMENTARY DATA. This sec¬
tion contains an error analysis of the various param¬
eters that affect bombing accuracy and applicable safe
separation data.

SECTION V, PLANNING PROCEDURES AND
SAMPLE PROBLEMS. This section contains a de¬
scription of all charts and ballistic tables used to
plan a non-nuclear mission. Sample problems are
provided to illustrate the use of the charts and the
planning procedures as outlined in the mission plan¬
ning form.

SECTION VI, PLANNING CHARTS AND TABLES.

This section contains the safe escape, fuze arming,
dive recovery, sight depression charts, blank mis¬
sion planning forms and other data required for mis¬
sion planning. All ballistic tables that provide
weapon range, time of fall. etc. are contained in
T.O. 1F-4C-34-1-2.

YOUR RESPONSIBILITY-LET US KNOW

Review conferences with operating personnel and a
constant review of accident and flight test reports as¬
sure inclusion of the latest data in the manual. In
this regard, it is essential that you do your part.
Comments, corrections, and questions regarding this
manual, other than deficiency reports, should be for¬
warded to AFATL (DLYE) Eglin Air Force Base,
Florida. The Air Force Armament Laboratory is the
Air Force Agency responsible for the technical con¬
tent of this manual. Deficiency reports on this man¬
ual shall be forwarded in accordance with T.O. 00-5-1.

AUTHORIZATION FOR LOCAL REPRODUCTION

Local reproduction of all charts, tables, forms, and
any data based on the content of this manual, the
classified supplements, and the checklist is autho¬
rized.

CHECKLIST

The Aircrew Weapon Delivery Checklist, T.O. 1F-
4C-34-1-1CL-1, contains the numbered and lettered
normal procedures and jettison procedures contained
in this manual and the classified supplements T.O.
1F-4C-34-1-1-1 and T.O. 1F-4C-34-1-1-2. Classi¬
fied terms and data is omitted from the checklist. A
complete and separate checklist is provided for each
non-nuclear weapon and each item of practice equip¬
ment. The format permits the aircrew to reduce the
volume of the checklist by removing the portions
that apply to the weapons or equipment not associ¬
ated with his model aircraft, mission being flown,
or his crew duty (i.e., The AC need not carry the
radar BIT checks, all tow target checks can be re¬
moved, etc).

CHANGE SYMBOL

The change symbol, as illustrated by the black line
in the outer margin of this paragraph, indicates sig¬
nificant text changes made to the current change or
revision. No change symbol is used to indicate
changes made to illustrations. This manual will be
changed every 90 days.

PUBLICATION DATE

The publication date that appears on the title page
represents the currency of the data contained in the
manual. When reference to this manual is made, the
publication date (which includes the date of the latest
change) should be used. (The publication date is not
the printing or distribution date.)

WARNINGS, CAUTIONS, AND NOTES

The following definitions apply to Warnings, Cautions
and Notes found throughout the manual.

WARNING

An operating procedure, practice, etc.,
which, if not correctly followed, could result
in personal injury or loss of life.

I CAUTION

An operating procedure, practice, etc.,
which, if not strictly observed, could result
in damage or distruction to equipment.

Note

An operating procedure, condition, etc.,
which, is essential to highlight.

iii

Change 8

T.O. 1F-4C-34-1-1

SAFETY AND OPERATIONAL SUPPLEMENT SUMMARY

The following list contains: previously cancelled or incorporated Supplements;
outstanding Supplements, if any; and Supplements incorporated in this issue. In
addition, space is provided to list those Supplements received since the latest
issue.

NUMBER

SUBJECT OR DISPOSITION

T.O. 1F-4C-34-1-1SS-1 thru -10

Previously Incorporated.

T.O. 1F-4C-34-1-1S-1 thru -42

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1F-4D-522 Mod 203 8D. Lor an-D for ad- 1 Jan 71

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T.O. 1F-4C-34-1-1

TABLE OF CONTENTS

PART 1. DESCRIPTION (F-4C)

PART 3. DESCRIPTION (F-4E)

Mission Description. 1-3

Aircraft Weapon System. 1-9

Jettison Controls. 1-19

Suspension Equipment. 1-21

AGM-12 Weapon System. 1-29

PART 2. DESCRIPTION (F-4D)

Mission Description. 1-36

Aircraft Weapon System Controls . . . 1-42

Weapon Delivery Modes . 1-61

Jettison Controls. 1-80

Suspension Equipment. 1-83

AGM-12 Weapon System. 1-93

Mission Description. 1-100

Aircraft Weapon System Controls . . . 1-106

Weapon Delivery Modes . 1-123

Jettison Controls. 1-144

Suspension Equipment... 1-146

AGM-12 Weapon System. 1-156

PART 4. DESCRIPTION (F-4C/D/E)

Combat Weapons.

Bomb Fuzes.

Training Weapons and Equipment. . . .
Combat Support Equipment.

1-1/(1-2 blank)

T.O. 1F-4C-34-1-1

PART 1 DESCRIPTION-^

TABLE OF CONTENTS

MISSION DESCRIPTION (F-4C)

Dive Bombing.1-3

Rocket Launch.1-5

Gun Firing.1-5

Level Bombing.1-5

Ripple Release Bombing.1-5

Low Drag Bomb Delivery.1-5

Fire Bomb Delivery.1-5

CBU Delivery.1-6

High Drag G.P. Bomb Delivery.1-7

Leaflet Bomb Delivery..1-7

Flare Dispensing.1-7

Loft Bombing.1-6

AIRCRAFT WEAPON SYSTEM CONTROL

(F-4C)

Multiple Weapons Controls.1-9

Gun Pod Controls.1-15

Loft Bombing Controls.1-16

JETTISON CONTROLS (F-4C)

Pylon/Suspension Equipment.1-19

Emergency Jettison.1-19

Selective Jettison.1-19

SUSPENSION EQUIPMENT (F-4C)

Conventional Weapon Suspension .... 1-21

BRU-5/A (Aero-27/A) Bomb Rack ... 1-26

MAU-12B/A Armament Pylons.1-26

Multiple Ejector Rack (MER).1-26

Triple Ejector Rack (TER).1-26

LAU-34/A Launcher.1-26

Rehoming MER'S and TER'S.1-27

Aero 7A Missile Launcher (AIM-7D/E

Missile).1-27

LAU-7/A Missile Launcher (Refer to
T.O. 1F-4C-34-1-1A)

AGM-12 WEAPONS SYSTEM (F-4C)

Mission Description.1-29

Configuration and Suspension.1-29

Aircraft Components.1-30

Missile Control.1-30

Cockpit Controls.1-33

AGM-45 WEAPON SYSTEM
(Refer to T.O. 1F-4C-34-1-1A)

FIRE CONTROL SYSTEM, AN/APQ-100
(Refer to T.O. 1F-4C-34-1-1A)

RADAR HOMING AND WARNING SYSTEM
(Refer to T.O. 1F-4C-34-1-1A)

MISSION DESCRIPTION (F-4C)

DIVE BOMBING

The dive bombing tables (for single release and rip¬
ple release) provide trajectory data for the various
parameters associated with delivery (figure 1-1).
Consistency in the all important roll-in parameter
cannot be overemphasized. The parameters of alti¬
tude, airspeed, distance from target, and power
setting are preplanned to place the aircraft at a pre¬
determined release altitude and distance from target
with a predetermined bomb release velocity and
attitude to effect an accurate hit. Because of the long
periods of wind effect on the trajectory of the bomb,
it is also important that the AC have knowledge of the
magnitude of wind effect and primarily the wind
velocity at release altitude.

The optical sight is used in conjunction with the al¬
timeter and the calibrated airspeed indicator to
determine the release point. The bombing tables pro¬
vide the sight depression angle relative to the flight
path. To obtain the actual sight setting, add the angle
of attack obtained from the angle-of-attack chart. In
addition to crosswind correction, the low altitude re¬
lease conditions require lateral offset of the flight
path to compensate for the location of the ejector

racks from the aircraft centerline, and to compen¬
sate for the lateral ejection of the bomb from the
ejector rack.

Several factors must be considered when determin¬
ing an indicated release altitude: altitude loss during
pullout, minimum aircraft ground clearance, altim¬
eter lag, altimeter position error, and target ele¬
vation. The altimeter is set according to target
pressure reduced to sea level (target altimeter set¬
ting).

Note

Neutral rudder trim should be accomplished
at the planned delivery speed. Since the turn
and slip indicator in the real’ cockpit is more
sensitive, the pilot should assist the AC by
calling the indicator display.

The bombing tables assume normal G loading for the
given dive angle which can be obtained only when a
wings-level, straight line flight path is maintained
prior to release. The pipper should be allowed to
walk toward the target or aimpoint and should arrive
when the aircraft is at the release altitude and air¬
speed.

Change 3

1-3

T.O. 1F-4C-34-1-1

DIVE DELIVERY

RELEASE ALTITUDE
START PULLOUT

TARGET _J— HORIZONTAL-

. - •

...... : . . : ■'

Figure 1-1

LEVEL DELIVERY

BOMB RELEASE

CBU DELIVERY

RELEASE PATTERN
OF ONE TUBE

Figure 1-2

1-4

T.O. 1F-4C-34-1-1

Immediately following bomb release, a preplanned
pullout is initiated. If buffet is encountered the
buffet boundary is maintained until the desired climb
attitude is obtained.

ROCKET LAUNCH

Rocket launching (figure 1-1) requires the same con¬
siderations with respect to roll-in position, rudder
trim, wind correction, release point, and pullout
maneuver.

Fuze arming is not a consideration for rocket launch
except when using the WDU-4/A Flechette Warhead;
refer to the confidential supplement for release con¬
siderations, section V. Safe escape considerations
are somewhat different in that the aircraft is flying
toward the frag envelope and possible secon¬
dary explosions from the target. The safe escape
tables in section VI do not consider terrain avoidance
nor secondary target explosions. The effect of wind
is less for rockets than for bombs because of the
shorter time of flight. The rocket launch tables
presented in T.O. 1F-4C-34-1-2 are valid for all
rocket launchers and type of suspension equipment
used. Separate launch tables are required for the
various categories of warhead used with the 2.75-inch
rocket motor.

GUN FIRING

Strafing with the SUU-16/A gun pod (figure 1-1) re¬
quires the same considerations with respect to roll-
in position, rudder trim, wind correction, release
point, and pullout maneuver. Inspection of the 20mm
ballistics tables indicates sight setting variations,
resulting from variations in speed and angle of attack,
are smaller than for rocket firing. For strafing,
variations in speed, firing altitude, and angle of at¬
tack are negligible; slant range is most important.

Safe escape consideration when firing the 20mm gun
must include terrain avoidance, ricochet, and sec¬
ondary target explosions. The delivery considera¬
tions for firing at a ground target are generally the
same as for bombing and rocket firing. Wind cor¬
rection and sight depression is less because of the
projectile's shorter time of flight. Like the rocket
launch tables, the sight setting is given as a func¬
tion of gross weight. Refer to the description of the
SUU-16/A gun pod and the 20mm ammunition.

LEVEL BOMBING

Level Bombing (figure 1-2) is a special case of dive
bombing where the dive angle is zero; the delivery
parameters are basically the same. The approach to
the target is performed at a constant altitude, wings
level, and at a stabilized airspeed. After bomb re¬
lease, the aircraft may continue the approach course
and speed or perform the required escape maneuver.
Refer to Safe Escape, section V. The most sensitive
parameters that affect bombing accuracy are the re¬
lease altitude above target and pitch attitude. The

method used to correct wind affects is determined by
the method of target tracking (crabbed or drifting)
and the type of weapon (high drag or low drag). Refer
to Wind Correction, section V.

RIPPLE RELEASE BOMBING

Ripple release bombing tables are provided in T.O.
1F-4C-34-1-2. Ripple release (figure 1-3) (dive or
level) delivery is identical to the single release with
the following additions:

a. Safe escape and dive recovery must be based on
the release altitude of the last bomb.

b. The sight setting or bomb range is computed to
place the center of the impact pattern on target.

c. Wind correction is based on the time-of-fall of
the first bomb released.

d. The minimum release altitude for a level ripple
release is based on a straight ahead escape.

e. During the ripple release, a straight line flight
path should be maintained. When the pipper is on
target, the bomb button is depressed. The pipper
will pass beyond the target during the ripple release.
If a straight line flight path is not observed prior to
and during the ripple release, the following adverse
conditions can be expected:

(1) Increased dive angle.

(2) Increased altitude lost during recovery.

(3) Reduced pattern length.

(4) Reduced G-loading.

(5) Possible bomb-to-aircraft collision.

LOW DRAG BOMB DELIVERY

Level bombing tables are provided in T.O. 1F-4C-
34-1-2. Lower Release altitudes can be used (i.e.,
500 feet) if full military power is selected and a 4.0G
pullup is initiated immediately after bomb release
to attain a 20’ to 30° climbing attitude. Refer to Safe
Escape, section V. Crosswind correction is not re¬
quired if the aircraft is crabbed to maintain a ground
track through the target. Rangewind correction is
not required if the bomb is released at a ground speed
that is equal to the preplanned true airspeed. Refer
to Wind Correction, section V.

Dive bombing tables are provided in T.O. 1F-4C-34-
1-2 for all the low drag bombs and the practice
bombs. Refer to Safe Escape, the Fuze Arming
charts, and Dive Recovery charts to determine the
minimum release altitudes.

FIRE BOMB DELIVERY

Level Bombing and dive bombing tables are provided
for dive angles from 0° to 45°. The sight depression
angle given in the table is computed to place the fire
bomb on target; when it is desirable for the fire
bomb to hit short of the target, the distance must be
estimated or the sight setting recomputed using the
Sight Depression charts, section VI. Wind correc¬
tions can be applied in the same manner as lor the

1-5

T.O. 1F-4C-34-1-1

RIPPLE RELEASE

DIVE DELIVERY

R] Range of First Bomb.

RN Range of Last Bomb.
ft Dive Angle.

Al Release Altitude of First Bomb.

AL Altitude Lost During Pullout.

A|*j Release Altitude of Last Bomb.

N Number of Bombs Released.

Rp Range from Release to center of pattern
SD Sight Depression.

Time of fall of first bomb.

IR Release Interval in Sec.

PL Pattern Length

Figure 1-3

low drag bombs. Refer to Wind Corrections, sec¬
tion V. The Dive Recovery chai'ts must be used to
determine the minimum release altitude.

DO NOT FLY through FIRE BOMB SMOKE
within 20 seconds of burst as a compressor
stall or flameout could occur.

CBU DELIVERY

The CBU delivery (figure 1-2) consists of a low level
or low angle approach to target at the predetermined
speed and altitude above target. Crosswind correc¬
tion is applied (in addition to crabbing the aircraft)
by offsetting the flight path parallel to, and upwind of
the no-wind ground track. Flight path offset, to cor¬
rect for crosswind, is required for the high-drag
CBU munitions because of its longer time of flight.
The optical sight is used to establish the release
point. Rangewind correction may be ignored for the
CBU delivery. The bombing tables provide the sight
depression angle from flight path that will place the
first bomblet 500 feet short of the target. Use the
Sight Depression charts, section VI when other than
500 feet short impact is required.

When the dive delivery is used, a straight line flight
path should be maintained during the release, and
for 2 seconds after release; the minimum release
altitude should be planned accordingly.

CBU DELIVERY USING THE SUU-7 DISPENSER

When a dive delivery is used for CBU series weapons
using the SUU-7 dispenser, a straight line flight
path should be maintained during the release and for
2 seconds after release. The minimum release al¬
titude should be based on altitude lost during re¬
covery plus altitude lost during the 2 second sta¬
bilized dive after release. This procedure is neces¬
sary to prevent voids in the bomb impact pattern
whether using dispensers with or without modified
tube extensions. The above procedures must be used
when the dispenser is not modified with tube exten¬
sions to prevent bomb hang-up and possible subse¬
quent early detonations.

Do not release bombs from unmodified SUU-7
dispensers (without tube extensions) while the
aircraft is in other than wings level stabilized
flight.

1-6

T.O. 1F-4C-34-1-1

HIGH DRAG GP BOMB DELIVERY

The high drag GP bombs can be delivered from alti¬
tudes between 100 feet to 3000 feet depending upon
the bomb used, the fuzing limitation, fragmentation
envelope and dive angle. The high drag characteris¬
tic provided by a retarder tail fin assembly reduces
the bomb range and increases the bomb time of fall
and impact angle. Single release bombing tables and
ripple release bombing tables are provided in T.O.
1F-4C-34-1-2. Use the Fuze Arming and Safe Es¬
cape chart, section VI.

WARNING

DO NOT FLY over or near burst area within
20 seconds of detonation as aircraft damage
can result from flying debris. During train¬
ing missions, at least 20-seconds spacing
between aircraft must be observed when
inert or sand filled bombs are released, hi
the training situation, observing the 20-sec¬
ond spacing between aircraft prevents a
bomb-to-aircraft collision in the event a
bomb releases low drag and ricochets into
the air after impact.

MK82 (SNAKEYE I) AND M117R HIGH/LOW DRAG
OPTION, IN-FLIGHT SELECTIVITY

The MK 82 (Snakeye I) and M117R GP bombs can be
released in a low drag configuration (retarding fins
remain closed) or a high drag configuration (retard¬
ing fins open after release) provided arming wire
routing is accomplished during loading to provide
these options. The high or low drag configuration is
selected in flight through the arm nose tail switch on
the multiple weapons control panel. Refer to Arming
Wire/Lanyard Routing, part 4, for detailed informa¬
tion concerning the required arming wire configura¬
tion for this capability.

For a high drag release using the in-flight option,
the NOSE & TAIL position is selected on the arm
nose tail switch. The NOSE position is selected for
a low drag release with only the nose fuze initiated.
After T.O. 1F-4-805, the TAIL position may be se¬
lected for a high-drag release with only the tail fuze
initiated.

WARNING

inflicted damage, injury to friendly ground
forces, single fuze reliability, and delivery
accuracy degradation before approving this
option for operational use.

Note

With the approved arming wire routing for
the in-flight high/low drag option, single
fuze reliability (nose fuze only) is available
with the low drag option. Dual fuzing relia¬
bility (nose and tail) is available with the re¬
tarded high drag option if the high drag bomb
time of fall exceeds 6.6 seconds. If the high
drag bomb time of fall is less than 6.6 sec¬
onds, only FMU-54 tail fuze arming is avail¬
able. Single fuze reliability (tail fuze only)
is available with the high drag option when
the arm nose tail switch is positioned to
TAIL.

WARNING

* When the MK 82 Snakeye I or M117R bombs
are configured for inflight selectivity for
high/low drag releases, the minimum nose
fuze setting is 6.0 seconds for the M904E2
or M904E3 fuze; the minimum tail fuze set¬
ting for the FMU-54 fuze is 2.5 seconds.

With current arming time tolerances, the
minimum bomb time of fall to provide time
for the fuzes to arm is 6.6 seconds for the
nose fuzes and 2.8 seconds for the tail fuze
(high drag arming only).

* Under combat conditions, where a 6 second
nose fuze arming delay setting may be incon¬
sistent with operational requirements, a 4
second M904E2/E3 nose fuze arming delay
setting may be used subject to the following
restrictions:

* Dive Releases. For planned high drag dive
releases, the release altitude must not ex¬
ceed 1000 ft AGL.

* WRCS Dive-Toss Releases. For planned high
drag dive toss releases, the pickle altitude
must not exceed 1000 ft AGL.

* Level Releases. For planned level releases
of high drag weapons and a straight and level
escape maneuver, the release altitude must
not exceed 250 ft AGL. This restriction does
not apply for a single, pairs or salvo type re¬
lease if a 4G wings level pullup or a 4G 60
banked turn escape maneuver is executed
immediately after release.

Change 9

1-6A

T.O. 1F-4C-34-1-1

Note

None of the foregoing restrictions apply if
the planned high drag bomb release altitudes
exceed the minimum release altitudes that
are required for safe escape for low drag
MK 82 bombs.

WARNING

With this in-flight option of high/low drag
selection, strict adherence to the prescribed
cockpit switchology is mandatory. If the AC
inadvertently selects high drag, or exper¬
iences an arming solenoid malfunction when
the intent is to release a low drag bomb, a

fully armed high drag bomb would impact
considerably short of the intended aimpoint.
If friendlies are in the immediate area, this
could result in disastrous consequences.
Conversely, if the AC inadvertently selects
low drag, or experiences an arming solenoid
malfunction when the intent is to release a
high drag bomb during close-in attack condi¬
tions, the result (if the bomb time of fall is
less than 6.6 seconds) would be an unarmed
bomb with an initial impact considerably
downrange of the intended impact point. This
could also result in disastrous consequences
if friendlies are in the area; particularly if
the bomb detonates, or ricochetes and then
detonates. If the bomb time of fall exceeds
6.6 seconds in this case, a fully armed low
drag bomb would impact considerably down-
range from the intended impact point.

1-6B

Change 9

T.O. 1F-4C-34-1-1

WARNING

* There is also a possibility of the delivery
aircraft suffering self-inflicted fragment
damage if an intended high drag bomb re -
leases low drag during a close-in attackcon-
dition, and for some reason detonated at
initial impact. To provide an additional mar¬
gin of safety in this event, the pilot should
execute a 4-G pullup or a 4-G, 60° banked
escape maneuver immediately after release.

• Minimum release altitudes with respect to
fragment envelope clearance should be ob¬
served even if the bomb is released SAFE.
This would protect the aircrew in the event
of an arming wire hang-up, solenoid mal¬
function, etc., resulting in an arming wire
being extracted and the bomb becoming fully
armed

Note

If the retarded bombs are configured to ex¬
clude any cockpit selection of a low drag
munition release, a 2.0-second nose fuze
arming delay setting may be used if nose
fuze arming wire withdrawal is initiated by
retarded fin opening action.

WARNING

If high drag ripple releases of the M117R or
MK 82 Snakeye I bombs are anticipated using
the in-flight high/low drag option selectivity,
the munitions must be loaded in the configu¬
ration specified in T.O. 1F-4C-1 for this
type release.

LEAFLET BOMB DELIVERY

The level delivery bombing mode is used to deliver
the M129E1, E2 leaflet bomb from release altitudes
of 4000 feet through 11,000 feet. The bombing table
in T.O. 1F-4C-34-1-2 states the bomb time of flight
and range from release to burst for a given level
flight release true airspeed and release altitude
above target. The time of flight is used to set the
mechanical time delay fuze for a 3000-foot detona¬
tion. The bomb range is used to estimate the re¬
lease point.

Wind effect on the bomb prior to burst is a function
of wind velocity and bomb time of flight. The wind
effect on the leaflets after detonation and during
descent is difficult, if not impossible to predict.

FLARE DISPENSING

The SUU-25A/A, B/A, C/A flare dispensers (figures
1-89, -90) are used to deliver the MK 24 flares. The
delivery aircraft approaches the target in level flight
at the preplanned release altitude. The MK 24 flare
profile and parameters are illustrated in figure 1-4.

Figure 1-4

Release airspeed is not a critical parameter. Re¬
lease altitude is critical only when it is desirable to
have flai-e burnout above the ground. The flare dis¬
pensing table (T.O. 1F-4C-34-1-2) provides the mini¬
mum release altitude AGL that will provide flare
burnout at impact. The desired burnout altitude AGL
must be added to the minimum release altitude AGL
to determine the actual release altitude AGL. The
flare dispensing table also provides the horizontal
distance traveled and vertical drop of the flare prior
to ignition. The flare ejection fuze delay time and
the flare ignition fuze delay time is set according to
the mission requirements and the data on the flai-e
dispensing table. To properly position the flare at
ignition, rangewind effect and crosswind offset (ft)
may be determined by multiplying the rangewind or
crosswind component (kts) times 1.7 times the sum
of the ejection and ignition fuze delay settings.

Change 9

1-7

LOn BOMBING

1. PRIOR TO TRP, SELECT LOFT DELIVERY MODE AND SET UP THE MULTIPLE WEAPON RELEASE MODE.

2 WHEN OVER TRP THE AC DEPRESSES AND HOLDS THE BOMB RELEASE BUTTON TO START THE PULLUP TIMER, THE PULLUP LIGHT ILLU¬
MINATES AND THE HORIZONTAL AND VERTICAL POINTERS ON THE ADI CENTER.

3 WHEN THE STEADY TONE SOUNDS AND THE PULLUP LIGHT GOES OUT, ADVANCE THROTTLES TO FULL MIL POWER AND BEGIN PULLUP. (WITH
THE MOTOR DRIVEN TIMER INSTALLED, A 0.25-SECOND WARNING TONE IS GIVEN PRIOR TO THE STEADY PULLUP SIGNAL.) FLY TO KEEP ADI
POINTERSCENTERED UNTIL BUFFET ONSET, THEN FOLLOW BUFFET BOUNDARY.

4 WHEN THE SELECTED RELEASE ANGLE IS ACHIEVED, THE PULLUP LIGHT ILLUMINATES. AND THE STEADY TONE STOPS. THE AC PLACES THE
MASTER ARM SWITCH TO ARM TO INITIATE RELEASE AND CONTINUES TO HOLD THE BOMB BUTTON DEPRESSED UNTIL THE LAST BOMB IS RE¬
LEASED.

5 WHEN THE LAST BOMB IS RELEASED, INITIATE A WINGOVER TO ACHIEVE A 120° TURN WHILE DIVING TO ESCAPE AT MINIMUM ALTITUDE.

F4C-34-I-127

Figure 1-5

LOFT BOMBING

The loft bombing mode combines the use of the mul¬
tiple weapons release system (MWRS) with the atti¬
tude reference and bombing computer set (ARBCS).
The purpose of the loft bombing mode is to provide a
ripple release capability of G.P. bombs from low al¬
titude with a minimum of aircraft exposure time to
ground-fire and without a target fly-over. This is
accomplished as illustrated in figure 1-5. Dui-ing
mission planning, an IP (identification point) is se¬
lected on the target map, or photos, that is located
near and on course to the target; the pullup point is
established; the release angle of the first and last
bomb, the pattern length of the bombs, and the pull-
up timer setting are also defined. Prior to the bomb¬
ing run, the following is accomplished.

a. The multiple weapons release system is set up
for a ripple release with the master arm switch in
OFF.

b. The LOFT bombing mode is selected on the bomb
control panel.

c. The low angle sector of the LABS bomb release
angle computer is set on the release angle of the
first bomb.

d. The PULLUP sector of the bombing timer is set
on the IP-to-pullup time.

At the IP, the bomb button (pickle button) is de¬
pressed and must be held energized until the final
bomb is released. Depressing the bomb button starts
the pullup timer. At the completion of the pullup
timer, a pullup signal is given and the AC begins a
programmed G pullup. When the aircraft attitude is
at the preselected angle, a release signal indication
is supplied. This is the signal to the AC to position
the master arm switch to ARM which initiates the
ripple release. The AC continues the pullup until the
last bomb is released. When the last bomb is rippled
off, the bomb button is released, and the AC begins a
wing-over escape maneuver to achieve a 120” turn
while diving to escape at minimum altitude.

The following is a more descriptive analysis of the
LOFT release system function. Either bomb button
(front or rear cockpit) is depressed over the IP.

This clutches the pullup timer and timer motor be¬
gins countdown. Bomb button power also energizes
relays which illuminates the pullup light, and moves
the horizontal and vertical pointers of the Attitude
Director Indicator (ADI) into view over the center o£

1-8

T.O. 1F-4C-34-1-1

the sphere. The vertical pointer indicates yaw/roll
flight deviations and the horizontal pointer shows
deviations from 1.0 G flight. The appearance of the
pointers indicates that the ARBCS has properly
switched into the LOFT bombing function. At the end
of the total time interval, pullup voltage is applied to
the tone generator producing a continuous audible
tone. The pullup light circuit is deenergized and the
light goes off. These are direct indications to begin
pullup. The AC should select MIL power and begin
rotation into the pullup maneuver. As the timer cir¬
cuits close, voltage is applied to one side of the low
and high angle release switches which are not yet
energized. Relays in the flight director bombing
computer are energized to start the G programer.
The ADI horizontal pointer now indicates G error
based on 4 G obtained in 2 seconds. The horizontal
pointer deflects upward unless the AC begins pullup.

Note

Refer to Bombing Timer (Dual Timer), this

section.

When the aircraft reaches the preset pitch attitude,
the release switch closes and the 28 volt dc power,
previously applied at pullup, becomes the release
signal. As release voltage is applied, the tone gen¬
erator is deenergized, the Break light above the ra¬
dar scope illuminates, and clutch voltage is removed
from the timer to reset the timer and allow the pull-
up light to illuminate. This is the signal for the AC
to position the master arm switch to ARM which
initiates the ripple release mode. Bombs are re¬
leased until the stations selected are empty or until
the bomb button is released. The AC continues to
hold the bomb button depressed and the G program

continues to be displayed by the ADI horizontal
pointer as an aid in completing the maneuver. The
vertical pointer is deflected out of view at release.

When the AC releases the bomb button, all bombing
voltage is removed and the horizontal pointer de¬
flects out of view, the Break light and the pullup light
go out. The only item remaining operational is the
timer motor, which is deenergized when the bomb
mode selector knob is placed to OFF.

Note

During the LOFT mode, once the bomb but¬
ton is depressed, it must remain depressed
until final bomb release. If the bomb button
is released before the first bomb is re¬
leased, an interlock circuit is energized and
the run cannot be continued by depressing
the bomb button. To overcome the interlock,
the bomb mode selector knob must be posi¬
tioned out of the LOFT function and then re¬
turned to LOFT.

The LADD bombing system can be used to perform
the loft bomb delivery. This is accomplished by se¬
lecting the LADD mode on the bomb mode selector
switch and setting the pullup-to-release time (from
the bombing tables) on the Release Timer, The re¬
lease signals are the same as for the loft bombing
mode. The horizontal needle on the ADI sphere will
program 3.5 G in 1.5 seconds (not 4.0 G in 2 seconds
as for the loft mode) until approximately 38° pitch
attitude is achieved. Therefore, the ADI cannot be
used above 38 J when the LADD bombing system is
used to accomplish the loft delivery; the aircraft ac¬
celerometer must be used to establish the pullup
acceleration.

AIRCRAFT WEAPON SYSTEM CONTROLS |F-4C)

MULTIPLE WEAPONS CONTROLS

The multiple weapons system provides the aircraft
with suspension and release capabilities for various
types of non-nuclear weapons. Figure 1-6 illustrates
the controls and indicators.

NORMAL RELEASE SEQUENCE

The normal release sequence is shown in figure 1-7.
The numbers indicate the release sequence when the
station selector switch is positioned on ALL BOMBS,
or when the stations are selected in the following se¬
quence: OUTBD WING, INBD WING, CTR. If the
order of station selection is not as stated, the num¬
bered order of release will change, but the sequence
(or chronological order) for the selected station re¬
mains the same. Note that when PAIRS is selected,
two bombs are released with each release signal
from the wings; however, the centerline station will
release only one bomb, rocket pod, or dispenser
with each release signal. Study the release sequence

of the MER and TER racks — this never changes. The
release signal steps over an empty point in the se¬
quence shown until it reaches a loaded point or, if
ALL BOMBS is selected, to another loaded station on
that wing. The arm nose tail selector switch must be
in NOSE & TAIL or NOSE when BOMBS are selected
to provide the auto-step feature. However, this is
not applicable to the MER-10A or the TER-9A racks.

Note

Refer to Suspension Equipment, this section,

for MER and TER rehoming procedures.

MULTIPLE WEAPONS CONTROL PANEL

The multiple weapons control panel (figure 1-6), is
directly below the front cockpit main instrument
panel. It contains switches which control and select all
phases of release or firing for the multiple weapons
system. A brief functional description of these
switches is contained in the following paragraphs.

1-9

T.O. 1F-4C-34-1-1

Weapon Selector Knob

The weapon selector knob, placarded WPN SEL, is a
rotary type switch with eight positions; only seven
positions are used. This switch is used to select the
type of munitions and method of release. The switch
positions are BOMBS-SINGLE, BOMBS-PAIRS,
BOMBS-RIPPLE, RKTS & DISP-SINGLE, RKTS &
DISP-PAIRS, GAM-83 (AGM-12), and AGM-45.

Note

•When the SUU-21/A dispenser is loaded on
the inboard stations (2 and 8), bomb release
will not occur if the weapon selector knob is
in RKTS & DISP. This is due to a pylon wir¬
ing modification for SUU-21/A dispenser car¬
riage on the inboard stations only. Release
or jettison of special weapons from an in¬
board station is not affected by this modifi¬
cation.

*When the weapon select knob is in the AGM-
45 position, IR missile status and the audio
tone is not available until the missile arm
switch is in ARM.

The only automatic mode of intervalometer operation
is BOMBS-RIPPLE. In the automatic mode, the
bomb button is depressed and held until the bomb re¬
lease sequence is complete. The manual mode re¬
quires that the bomb button be actuated for each
release.

The GAM-83 (AGM-12) position supplies release
power to the stations selected regardless of the type
of weapon loaded on the station. If a station is se¬
lected that contains a MER or TER rack with bombs
or rocket launchers, a bomb, a rocket launcher, or
a dispenser will be released when the bomb release
button is depressed (the rocket launcher or dispenser
will not fire). The GAM-83 position produces the
same effect as BOMBS-SINGLE. The converse is not
true; the GAM-83 (AGM-12/B) cannot be launched by
selecting BOMBS or RKTS & DISP. Refer to AGM-12
Weapon System, this section.

WARNING

Bombs or rocket launchers can be released
when the weapon selector knob is in the
GAM-83 position.

GAM-Auxiliary Switch

The GAM-auxiliary (GAM-AUX) switch, is a three
position switch marked INTERRUPT, NORM, and
TEST. The switch is in the AN/ARW-77 transmitter
network and is used only when the AGM-12B, -12C,
or -12E missile is aboard the aircraft. Refer to
AGM-12 weapon system, this section.

Master Arm Switch

The master arm switch, placarded MA, controls the
bomb button transfer relay, the arm nose tail selec¬
tor switch and the station selector knob. When this
switch is placed from SAFE to ARM, the transfer re¬
lay is energized and transfers the function of the
bomb button from the nuclear release system to the
multiple weapon system, provided the nuclear re¬
lease system is not energized. The switch must be
in ARM to effect firing or release of non-nuclear
bombs and rockets through the normal release mode.
The switch may be in either SAFE or ARM operation
for the SUU-21/A dispensers. The switch receives
power from the bomb arm circuit breaker, No. 1
panel.

Step Switch

The step switch is a two-position switch spring loaded
to NORMAL. Placing the switch in RESET, directs
the next release pulse to a left wing station. It will
not step a release pulse over to the right side. To
accomplish this:

a. Master arm switch - ARM

b. Weapon selector knob - BOMBS-SINGLE

c. Station selector knob - OFF

d. Step switch - RESET

This ensures the pulse is on the left side.

e. Bomb button - DEPRESS

The bomb button is the only method of directing
the next pulse to the right wing. With the sta¬
tion selector knob in OFF, the possibility of an
inadvertent bomb release is prevented.

Arm Nose Tail Switch

This switch (figure 1-6) completes the circuit be¬
tween the master arm switch and the arming solen¬
oids in the aircraft ejector racks (MAU-12, BRU-
5/A, and MER/TER). The energized solenoids re¬
tain the arming wire swivel loops and as munitions
are ejected, the arming wires are pulled to initiate
the fuze arming sequence. In the SAFE position, the
arming wires are retained by the munition during
separation from the aircraft and the associated fuze
remains SAFE.

1-10

Change 4

"All data on pages 1-10A thru 1-10B deleted.

T.O. 1F-4C-34-1-1

The arm nose tail switch also provides the selective
high/low drag capability for those weapons which
may be rigged for either a freefall or retarded drop.
In this case, the solenoids are energized to apply
the holding force for the lanyards which deploy the
retardation device. (Refer to M117R and MK 82
Snakeye I bombs, and Arming Wire/Lanyard Routing,
part 4.)

If this switch is used to select the M117R or
MK 82 (Snakeye I) high/low drag release op¬
tion in flight, the warnings and notes listed
in Mission Description, High Drag GP Bomb
Delivery, must be carefully observed.

The switch positions and corresponding solenoids
armed are shown below.

Switch Position Solenoid Armed

SAFE None

NOSE Fwd and Ctr

TAIL Aft

NOSE & TAIL Fwd, Ctr, and Aft

There is no center solenoid on the MER/TER and
BRU-5/A ejector racks.

With MER/TER equipment that do not have automatic
homing, the arm nose tail switch must be in the
NOSE or NOSE & TAIL position to apply power
through the sensing switch to the MER/TER stepper
solenoid. Then with a partial load of bombs aboard,
the empty stations are bypassed and the AC releases
one bomb with each pickle signal. The TAIL position
does not apply the stepping voltage and an extra
pickle must be delivered to step through each empty
MER/TER station.

With MER-10A and TER-9A equipment that have
automatic homing, empty stations are bypassed re¬
gardless of the arm nose tail switch position.

Interval Switch

The interval switch is used only during BOMBS/
RIPPLE, BOMBS/TRIPLE, and RKTS & DISP/RIP-
PLE modes on the weapon selector knob to estab¬
lish interval between each release. The switch has

three positions (0.06 SEC, 0.10 SEC, and 0.14 SEC)
that determine the pulse interval: the pulse length or
duration is always the same (23 to 33 milliseconds).
The pulse rate is measured from the start of each
pulse and therefore includes the pulse duration. The
pulse rate tolerance of the various i-elease intervals
are: 60 to 90, 100 to 115, and 140 to 161 millisec¬
onds.

Station Selector Knob

The station selector knob placarded STA SEL, is a
rotary type switch with eight positions. Only five
positions are used. The switch is used to select the
multiple weapons station, or stations, from which
the munitions are to be released or fired. The
switch positions are: OFF, OUTBDWING, INBD
WING, CTR, and ALL BOMBS. The OUTBD WING
position for example, selects both (and only) out¬
board station munitions for release. The CTR posi¬
tion selects only the centerline munitions. Figure
1-7 shows the MER/TER release signal sequence for
singles, pairs, and ripple methods, and for any sta¬
tion select position. The sequence for the ALL
BOMBS position, however, applies only the BOMBS
position on the weapon selector. When the weapon
selector knob is in one of the RKTS & DISP positions,
only the outboard MERS are selected; neither the
rocket launchers, nor any CBU dispensers located on
the inboard or centerline stations are selected by the
ALL BOMBS position. The release sequence for the
AGM-12 missile is described in later paragraphs.
For the AGM-45A, refer to T.O. 1F-4C-34-1-1A.

Note

On F-4C aircraft that have the AGM-45 capa¬
bility, a possible inadvertent conventional
stores release situation exists. With a mixed
load condition such as an AGM-45 or special
weapon on one inboard station and with a
conventional store on the other inboard sta¬
tion, it is possible to release the conventional
store while launching the AGM-45 or special
weapon. The inadvertent release possibility
exists if a dual timer release mode is select¬
ed, or if an AGM-45/DIRECT launch mode is
selected. Therefore, in situations where
such a configuration exists, maintain the
pedestal panel station select knob OFF to
avoid an inadvertent release of conventional
stores.

Bomb Button

Depressing the bomb button (figure 1-6) in either
cockpit, applies normal release voltage for all air-

Change6

1-11

CONTROLS AND INDICATORS

STATUS

MISSILE

SELECTED I

READY 1

READY

! SW/SW

sw/sw

( SELECTED |

SELECTED

,gam-auA\ma

^ntcrrupt>\rm

WPN

S 4 L V

READY

>RM NORMAL .14 SEC

on mss

H VDM?&SS_
PM. * 1000

HYP PfiiSS

NO.2 CONTROL

UTILITY

N01 CONTROL

ML INKINO -PART IMFtY
STEADY -EMPTY

RETICLE

DEPRESSION

KNOB

TRIGGER

SHADE CONTROL

BREAK

& LAMP BUTTON

OPTICAL SIGHT UNIT

CONTROL

STICK

MASTER ARM SW,

ARM NOSE/TAIL SW.

INTERVAL SW.

MISSILE STATUS PANEL

ST A.

SELECTOR

KNOB

WEAPON

SELECTOR

KNOB

MULTIPLE WEAPONS CONTROL PANEL

CLUSTER BOMB UNIT
CONTROL PANEL

Figure 1-6 (Sheet 1 of 2)

CONTROLS

EXT STORES
EMERREl

INOtCAlOR

PROTRUDING

STEPS UP

AUTO

ClEAR

safe safe

CENTER OUTBD

GUNS

55^ RESET
AIR REFUEL

STEPS DOWN

INDICATOR

flUSH

WING

STA

OW HIGH

AURALTONE

CONTROL

Off

jCOOLANT

CONTROL

sidewinder

WING

® CENTER STA

>•-' (CONTINUED)

GUN STATION
SELECTOR
SWITCHES

GUN

CLEAR

SWITCH

EXT. STORES EMERGENCY
RELEASE
(Panic Button)

AUXILIARY ARMAMENT CONTROL PANEL
(Guns and Sidewinder)

CENTER and WING STATIONS

Jettison Switch

jo|o|o|o !)

LOW ANGLE

HIGH ANGLE

PULL UP TONE

,'bombing TIMER

C PUll UP

-2JL2J3

STATION SELECTION

* NUCl
STORE
CONSENT

BOMBING TIMER
PUU UP RELEASE
lO'O'O (OiO'O

SECONDS

BOMB MODE
SELECTOR KNOB

PULL UP TONE
SWITCH

BOMB RELEASE
Angle Computer

BOMB CONTROL PANEL

BOMBING TIMER
(Motor Driven)

NUCLEAR STORE
Consent Switch

\ ion

NUCl '

STORES \\

/Jl,

L— 1

, ’V '

| | BOMB CONTROL ’

Solid State Timer Replaces
Motor Driven Timer

BOMBING TIMER
(Solid State)

4C-34-l-l-(9-2)

Figure 1-6 (Sheet 2 of 2)

Change 3

1-13

T.O. 1F-4C-34-1-1

to-ground weapons selected on the multiple weapons
control panel or the DCU-94/A monitor-control panel.
Power can be removed from the bomb release button
by pulling the A/G weapon release cont circuit
breaker, No. 1 panel.

BOMB BUTTON TRANSFER RELAY

The bomb button transfer relay transfers the release
signal, when energized, from the DCU-94/A panel
to the multiple weapons control panel. The relay is
energized when the master arm switch is positioned
to ARM, provided one of the following switches is
positioned AFT or SAFE:

a. DCU-94/A all station selector switches - AFT

b. DCU-94/A master release lock switch - AFT

c. Nuclear store consent switch - SAFE

CBU PANEL

The cluster bomb unit (CBU) panel (figure 1-6) is in
the forward cockpit right console. It contains five
station lights marked LO, LI, CTR, RI, and RO.
When any dispenser on a station has two releases re¬
maining, the light for that station begins flashing.
When all the dispensers contained on a station are
empty, the light illuminates steady. The CBU panel
is functional only when the weapon selector knob is
in RKTS & DISP, and all MER and TER stow plugs
are installed. The lights are connected to the warn¬
ing light dim and test circuitry when CBU's are
aboard.

WARNING

The empty CBU indication establishes that
all explosive detents in the CBU have been
fired. The possibility of a hung bomblet(s)
remaining in the tube(s) cannot be assessed
by the aircrew.

Note

The TER-9A and the MER-10A do not have
the CBU flasher circuits.

FOLD-DOWN OPTICAL SIGHT

The optical sight (figure 1-6) provides the AC with
a visual sight reference for bombing, missile launch¬
ing, strafing, and rocket firing. The sight is mounted
on the top center portion of the main instrument
panel and incorporates an adjustable combining glass
which is used to reflect a reticle image. This reticle
image consists of a 2-mil diameter pipper (aim dot),
and 20, 40 and 60-mil diameter segmented circles.

Control of the reticle image is achieved by rotating
the reticle depression knob located on the left side of
the sight. The scale is calibrated in 2-mil units and
provides angles of depression from 0 to 280 mils.
The SW position, or radar boresight line, is de¬
pressed 2° (35 mils) below the fuselage reference

line. The unit of measurement used to calibrate the
sight is: 1° = 17.45 mils, or 1 mil = 0.0573°. The
reticle image cannot be manually adjusted in azimuth.

The intensity (brightness) of the reticle image is con¬
trolled by the reticle illumination knob. Rotating the
knob in either direction from OFF, controls a dual
filament reticle lamp which projects the reticle im¬
age on the combining glass.

Note

The bottom filament should be used first.

The bottom filament is selected by rotating
the reticle illumination knob counterclock¬
wise (left).

Optical Sight Components

The optical sight is a collimating, reflector type, op¬
tical system which provides a sight line by projecting
a reticle image to infinity so that the image appears
to remain in a fixed position relative to distant ob¬
jects or targets. The sight basically contains the
following:

a. A two-filament reticle lamp with an On/Off dim¬
mer control.

b. A light diffusing lens.

c. A mirror mounted in a focus adjustment assem¬
bly.

d. A reticle pattern assembly.

e. An objective (collimating) lens system.

f. A reflector plate (combining glass) assembly
which may be folded down.

g. A manual elevation offset system (reticle depres¬
sion control).

h. A manually operated shade control.

Reticle Lamp

The reticle lamp contains two-filaments, which are
illuminated individually by rotating the control knob
in either direction from OFF. The magnitude of the
control knob rotation in either direction controls the
intensity (brightness) of the selected filament.

Diffuser Lens

The light rays from the reticle lamp are diffused by
the diffuser lens to provide uniform illumination of
the reticle pattern.

Reticle Pattern Assembly

The light rays from the diffuser lens pass through
the reticle assembly, which contains a pattern disc.
The pattern disc produces a reticle image, consist¬
ing of the 20, 40 and 60-mil diameter circles and
the two-mil aim dot (also referred to as a pipper or
tracking index).

Mirror Assembly

The reticle pattern is projected into the mirror as¬
sembly, focused, and reflected through the objective
lens located on the top of the sight.

1-14

T.O. 1F-4C-34-1-1

Collimating Lens

The objective lens collimates and projects the reticle
image onto the inner surface of the combining glass.
Since all light rays from any one point on the reticle
image have been collimated, they emerge from the
lens system as parallel rays focused at optical in¬
finity.

When the sight combining glass is to be folded
down, grasp the fold-down lever (figure 1-6)
rather than any part of the combining glass.
Otherwise, damage may occur in the de¬
pression knob gear train resulting in a con¬
siderable sight depression error.

Combining Glass

The collimated light rays from the objective lens are
reflected to the eye by the combining glass (reflector
plate). Since all the light rays from any one point on
the reticle image are parallel, the point appears to
be at an infinite distance and seems to remain in a
fixed position when the AC line of vision is anywhere
within the parallel rays. Light rays from a distance
object, or target, are transmitted through the com¬
bining glass to the eye. Since the rays from the tar¬
get are also parallel, the reticle image will appear
to be superimposed on the target or object.

GUN POD CONTROLS

The SUU-16/A and SUU-23/A gun pod control switches
(figure 1-6) are on the guns and sidewinder panel,
the multiple weapons control panel, and the front
cockpit control stick. Refer to SUU-16/A and SUU-
23/A description for specific differences.

MASTER ARM SWITCH

The master arm switch is on the multiple weapons
control panel. When the master arm switch is in
ARM and the landing gear handle is UP, power is
available at the gun station selector switches. When
the master arm switch is in ARM, the bomb button
transfer relay is energized if one of the three nuclear
release switches is off or safe.

GUN STATION SELECTOR SWITCHES

The gun station selector switches are on the auxil¬
iary armament control panel (guns and sidewinder
panel). The outboard station selector switch controls
the left and right wing gun pods. When the trigger
switch is actuated, both wing station gun pods fire
simultaneously. The center station switch controls
the centerline gun pod. When the respective station
selector switch is positioned to READY (MA switch
ARM) power is supplied to the gun pod, and the ram
air turbine (RAT) is extended into the airstream.
When the MA switch or the station selector switch is
positioned to SAFE, power continues to be applied
to the gun pod while the RAT is retracting. Power is
automatically removed from the gun pod when the
RAT is fully retracted.

GUN CLEAR SWITCH

The gun clear switch on the guns and sidewinder
panel, selects the gun mode of operation. When the
auto clear mode is used, unfired rounds are extracted
from the gun and ejected overboard. When the non-
clear mode is used, the unfired rounds remain in
the gun. The NONCLEAR position is selected when
the gun is to be fired in short bursts. The gun auto¬
matically switches to auto clear mode when the last
round is fired in the nonclear mode. When the guns
have been fired with the gun clear switch in the
NONCLEAR position and not completely fired out, a
final burst must be fired with the switch positioned
to AUTO CLEAR to clear the guns. If the gun is
fired out with the gun clear switch in the NONCLEAR
position, the bolt assemblies automatically clear.

TRIGGER SWITCH

The front cockpit trigger switch is on the control
stick. When the spring-loaded switch is actuated,
power is supplied to the clutch/brake solenoid to
initiate gun rotation and start the ammunition feed
system. The gun starts firing after the trigger switch
is pulled and ceases firing after the trigger switch is
released. Power can be removed from the trigger
switch by pulling the gun power circuit breaker, No. 1
panel. The trigger switch in the rear cockpit is al¬
ways inoperative. Refer to SUU-16/A Gun Pod, this
section. For missile launching, refer to T.O. 1F-
4C-34-1-1A.

WARNING

The trigger switch requires very little move¬
ment to initiate gun firing; therefore, the AC
should touch the trigger only when the gun is
to be fired.

TRIGGER TRANSFER RELAY

The trigger transfer relay must be energized to fire
guns and must be deenergized to launch air-to-air
missiles. To fire guns, the trigger transfer relay
is energized by selecting guns on the auxiliary ar¬
mament control panel (either center or outboard),
placing the master arm switch to ARM, and closing
the nose gear up limit switch (nose-gear up and
locked).

Note

*The nose gear up limit switch must be ener¬
gized to fire the outboard and the centerline
gun pods.

• When the trigger transfer relay is ener¬
gized, all missile status lights on the mis¬
sile status panel go out. The TK light re¬
mains on if the tank aboard relay is ener¬
gized. The tuned-up status of the missiles
is not affected.

1-15

T.O. 1F-4C-34-1-1

To launch air-to-air missiles, the trigger transfer
relay must be deenergized; the relay is deenergized by
positioning the master arm switch to SAFE.

LOFT BOMBING CONTROLS

The loft bombing delivery mode utilizes the following
controls and indicators.

a. Attitude director indicator (ADI).

b. Accelerometer.

c. Pullup light.

d. Bomb release angle computer (Low Angle)

e. Bombing timer (Pullup Timer).

f. Bomb control panel.

g. Multiple weapons control panel (dog bone).

h. Bomb release button (pickle button).

ATTITUDE DIRECTOR INDICATOR (ADI)

The ADI aids the AC in establishing and maintaining
a constant G pullup maneuver. The pointers are
programmed to move out of center when the aircraft
is not following the programmed pullup profile of
4.0 G obtained in 2 seconds and maintained there¬
after, and a wings-level pullup. When the loft bomb¬
ing mode is performed by using a pullup acceleration
of 3.0 G obtained in 2 seconds, the ADI should not be
used; use the aircraft accelerometer.

During the loft bomb run with the bomb mode switch
on LOFT, the vertical and horizontal pointers pro¬
gram the flight path. Prior to actuating the bomb
button, the vertical needle is deflected out of view if
the navigation function selector knob is in the ATT
position. When the bomb button is depressed, the
vertical pointer centers —presenting the roll signal
and indicating flight path deviations while the pullup
timer is operating. At pullup, when the pullup timer
is complete, the resolved yaw/roll signal is pre¬
sented on the vertical pointer. If the pointer deflects
to the right during the pullup, the AC rolls to the
right—correcting into the pointer. The vertical
director warning flag appears or disappears to indi¬
cate the degree of TACAN signal strength. There¬
fore, the appearance of the flap has no meaning with
respect to the vertical pointer in a bombing mode.

Note

The vertical pointer on the ADI is not in the
LABS yaw/roll network if the weapon selector
knob is in the AGM-45 position, except when
reject switch on the pedestal panel is in the
DF REJ position.

The horizontal pointer is always deflected out of view
unless the loft bomb run is in progress (bomb button
depressed). The pointer indicates deviations in the
1.0 G flight path during the low level approach to the
pullup point. When the pullup timer is complete,
horizontal pointer movement represents error be¬
tween the desired pullup G program and actual load
factor which is measured by the accelerometer. Note
that the system actually programs the proper G buildup
rate, which means that if the pilot increases G load¬

ing at the proper rate, the pointer will never move
from the center of the sphere. The pointer continues
showing error in the constant 4.0 G flight path until
the AC releases the bomb button after final bomb re¬
lease.

The ADI OFF flag comes into view if: (1) a system
ac or dc power failure occurs; (2) there is excessive
error in the roll and pitch signal sources of the gyro¬
scope assembly; (3) an ADI failure, or an internal dc
failure within the ADI occurs. The OFF flag indicates
malfunctions of the ARBCS only, regardless of the
mode the AC has selected (PRIM or STBY) on the
compass control panel. If the gyro system fails in
some manner (as suggested by conditions 1 and 2
above), the aircrew cannot expect to obtain an accu¬
rate bomb release angle since release occurs through
the ARBCS pitch-following system.

BOMB RELEASE ANGLE COMPUTER

The release angle computer contains the high and low
angle release switches, the drum shaft and yaw/roll
resolver, and the drogue switch. The pitch inputs
drive the drum shaft which actuates the high and low
angle release switches. The yaw and roll inputs are
resolved, as a function of pitch, and transmitted to
the flight director bombing computer for use in the
vertical director pointer network. The controls on
the front of the computer are available in the rear
cockpit. The Low Angle control may be set from 0°
to 89.9° and the High Angle control may be set from
70° to 179.9°. Only the Low Angle control is used for
loft bombing.

WARNING

When the LABS release angle gyro is set
greater than 169.0°, bomb release may oc¬
cur at the pullup point when the bomb button
is depressed (INST O/S) or at the comple¬
tion of the pullup bombing timer (TIMED
O/S).

FLIGHT DIRECTOR BOMBING COMPUTER

This unit develops dc voltages, which are propor¬
tional to yaw/roll and G error, for steering indica¬
tions in the loft bombing maneuver. The unit also
contains the tone generator which provides the warn¬
ing and pullup tone in the headset. By removing a
cover plate, controls are available to set tone level,
roll sensitivity, yaw sensitivity, and pitch and G
error sensitivity. The sensitivity controls govern
the ADI horizontal and vertical pointer rate of de¬
flection with respect to yaw/roll and G error signals.
The flight director computer contains a roll cancel
relay which is energized if roll error (yaw/heading
change) exceeds 30° during the pullup flight path.

With the roll cancel circuit energized, the release
circuit cannot be energized and the bomb run is can¬
celled. To ready the system for another run, mo¬
mentarily position the bomb mode switch out of the
selected function than back to LOFT.

1-16

NORMAL RELEASE SEQUENCE

SINGLES/RIPPLE

PAIRS

'' HI

i Sg

•

LlliV |il

fenl:

22J20J

24W

21 X 19 T

23ji

T.O. 1F-4C-34-1-1

BOMBING TIMER (DUAL TIMER)

The dual timer controls include the pullup and release
timer controls in the rear cockpit. The pullup timer
may be set from Oto 60 seconds and the release timer
may be set from 0 to 30 seconds. Both timers are
settable in increments of 0.1 seconds with 0.1 second
as the minimum numerical setting. The setting ref¬
erences in the windows do not move during the appli¬
cation of operate voltage in the bomb run. Completion
of the pullup timer energizes relays which provide the
various pullup signals and the pullup flight program.
The timers are either motor driven or solid state.
The motor driven timer receives 115 volt ac power
and incorporates a pullup warning tone. The solid
state timer receives 28 volt dc and has no warning
tone signal. Timer excitation voltage is applied when
the AC selects any mode except DIRECT. Timer
initiate (operate) voltage is applied, however, as a
function of the specific mode selected. To demon¬
strate, the following list summarizes the timer oper¬
ated versus the mode selected. (Operate voltage is
applied by actuating the bomb button.)

a. LOFT, TIMED O/S -

Operate voltage is applied only to the PULLUP
timer, provided the timer is set to some value
other than zero. The PULLUP timer must be
set to some value to energize the ADI pullup
flight path program.

b. TIMED LEVEL and TIMED LADD -

Operate voltage is applied to the PULLUP
timer; then to RELEASE timer at the termina¬
tion of the PULLUP timer countdown. For the
LADD mode, the PULLUP timer must be set
on some value to get the ADI pullup schedule,
the RELEASE timer must be set to develop a
bomb release signal.

c. INST O/S -

Operate voltage is not applied to either timer.

d. Pullup Warning Tone -

(1) Motor Driven Timer: For all modes in which
the PULLUP timer is set, a 0.25 second
warning tone pulse is initiated 1 second before
PULLUP timer completion.

(2) Solid State Timer: A warning tone pulse is
not provided.

PULLUP TONE CUT OFF SWITCH

The pullup tone cut-off switch is added to all aircraft
on the left console, rear cockpit. The switch pre¬
cludes external transmission of the audio tone during
any bombing mode in which the tone signal is in¬
volved. With the switch in TONE ON, the audio tone
signal is transmitted through the UHF transmitter;
the TONE OFF position deenergizes the same tone-
transmit circuit. In either case, the aircrew hears
the tone and all tone functions remain the same.

1-18

Change 3

T.O. 1F-4C-34-1-1

JETTISON CONTROLS |F-4C|

Note

Refer to Jettison Procedures, section HI.

PYLON/SUSPENSION EQUIPMENT

The wing station (MAU-12) armament pylons cannot
be jettisoned from the aircraft. The jettison controls
jettison the MER, TER, or weapons suspended di¬
rectly from the armament pylons. The LAU-34/A
launcher, used to suspend and launch the AGM-45
and the AGM-12B, cannot be jettisoned: the jettison
controls jettison the missile from the launcher with¬
out motor ignition. The LAU-7A/A launchers used to
suspend and launch the AIM-9 are bolted to the in¬
board armament pylon and cannot be jettisoned; the
applicable jettison controls launch the AIM-9 mis¬
siles or the TDU-ll/B target rockets with motor ig¬
nition. When the inflight lockout pins are installed,
the LO, LI and RI Unlocked lights on the DCU-94/A
control-monitor illuminate. The RO Unlocked light
will not illuminate when the lockout pin is installed.

EMERGENCY JETTISON

EXTERNAL STORES EMERGENCY RELEASE BUTTON

The external stores emergency release button is a
momentary contact, pushbutton switch used to jetti¬
son all stations simultaneously. This control may be

referred to as the panic button. The button is in the
front cockpit on the left vertical panel. Jettison
procedures and the conditions are contained in sec¬
tion III.

SELECTIVE JETTISON

CENTERLINE STATION JETTISON

The centerline station jettison switch is a cover-
guarded switch on the fuel control panel. The switch
has two positions: NORM and JETT. The switch is
spring-loaded to NORM. Placing the switch to JETT
supplies jettison voltage to the centerline station.
Refer to section in, Jettison Procedures.

INBOARD WING STATION (MISSILE JETTISON
SELECTOR)

The missile jettison selector knob is a rotary type
pushbutton switch on the missile status panel. This
switch provides selective jettison of the inboard
wing stations. The switch positions are as follows:
OFF, R FWD, R WING, R AFT, ALL, L AFT,

L WING, and L FWD. Jettison voltage is supplied to
the left or right inboard stations by selecting
L WING or R WING, and pushing the jettison button.
Refer to section IE, Jettison Procedures.

Change 5

1-19

T.O. 1F-4C-34-1-1

OUTBOARD WING STATION JETTISON

The wing station jettison switch (figure 1-8) placarded
WING STA JETT, is a cover-guarded, momentary
contact switch, spring-loaded to NORM. The switch is
on the fuel control panel. The switch has two positions:
NORM and JETT. Placing the switch to JETT sup¬
plies jettison voltage to the left and right outboard
wing stations. Refer to section HI, Jettison Proce¬
dures.

Outboard Station Selective Jettison
(After T.O. 1F-4-863)

The outboard pylon jettison select switch (figure 1-8)
provides a selective jettison function for the out¬
board wing stations. The switch is positioned to
either LEFT, RIGHT, or BOTH, and then the wing
station jettison switch is energized to jettison the
contents of the outboard station(s). This is actually
a five-position switch with two positions not plac¬
arded. The center (straight up) position is OFF; the
inboard position is not in use and is essentially
another OFF position. Selecting either of these
(OFF) positions disable the wing station jettison
switch. The selective LEFT and RIGHT positions
enable the AC to meet specific jettison limitation re¬
quirements if an unsymmetrical external store load
exists on the outboard stations.

ARMAMENT SAFETY OVERRIDE PANEL

The armament safety override button is a push type
switch consisting of a holding coil and three individ¬
ual double pole switches ganged together by a com¬
mon plunger shaft and is spring-loaded to OFF.

When the override button is depressed, 28v dc is di¬
rected to the holding coil which retains the button de¬
pressed. This bypasses the interlock in the landing
gear handle and the release and jettison circuits are
placed in an inflight configuration.

WARNING

With the armament override button depressed,
a hazard exists if a centerline station fuel
tank is jettisoned on the take-off roll.

Note

If necessary during flight, the override but¬
ton may be manually held depressed to effect
a jettison or release.

LANDING GEAR CONTROL HANDLE

The landing gear control safety switch is integral
with the landing gear control handle and is used to
prevent the inadvertent application of electrical power
to the armament circuits. When the gear handle is
UP, this switch directs electrical power from the
R 28v dc bus to the No. 1 miscellaneous relay panel,
closing the armament bus relay. The armament bus
relay then supplies electrical power to the armament
circuits. When the gear handle is DOWN, power is
applied through the safety switch to the armament

safety override button holding coil; thus, the arma¬
ment safety override button remains pulled in when
depressed.

LEFT MAIN GEAR SCISSORS SWITCH

The left main gear scissor switch is mounted on the
left main gear strut and is actuated by a cam on the
bottom of the gear scissor hinge. When the strut ex¬
tends, the scissor links spread and the cam rotates
against the scissor switch, depressing the plunger.
The scissor switch makes contact when the plunger
is depressed. The switch when closed, allows elec¬
trical power to go from essential 28v dc bus to the
external stores jettison switch, centerline tank jetti¬
son switch, and the nuclear weapons jettison switch.
The armament safety override button bypasses the
gear scissor switch and supplies electrical power to
the jettison and release circuits for ground operation

NUCLEAR STORES RELEASE AND JETTISON

Most equipment suspended from both inboard arma¬
ment pylons, the left outboard armament pylon and
the Aero 27A centerline bomb rack can be jettisoned
through the nuclear store release circuit DIRECT
release mode. This is accomplished through the
DCU-94/A control monitor and the bomb release
button. Refer to section III for procedures. The
nuclear release circuit (DIRECT mode) will not jetti¬
son the left outboard MER when the MER is shifted
aft. The nuclear jettison circuit (NUCLEAR PUSH
TO JETT) will jettison a left/aft shifted outboard
MER. However, the right outboard station could also
jettison even though only the left outboard station is
selected on the DCU-94/A.

pCAUTION^

In aircraft with T.O. 1F-4-801, the nuclear
store release and jettison circuit should not
be used for selective jettison from a partic¬
ular station. The nuclear store jettison but¬
ton (NUCLEAR PUSH TO JETT) should be
used as a last resort, and only when the in¬
advertent jettison from unselected stations
is of little concern. For example, the fuse¬
lage missiles may jettison and both inboard
stations and CL station may jettison, even
though only the right or left inboard station
is selected on the DCU-94/A. Both outboard
stations and CL station may jettison even
though only the left outboard station is se¬
lected on the DCU-94/A. When only the cen¬
terline station is selected, only the center-
line station is expected to jettison.

ECM POD JETTISON

On F-4C aircraft after T.O. 1F-4C-598, provisions
for ECM pods are added on stations 2, 4, 5, 6, and 8.
Prior to this, only station 9 had provisions for an

1-20

Change 8

T.O. 1F-4C-34-1-1

MISSILE JETTISON
SELECTOR KNOB

WING STA
JETT SWITCH

OUTBD

PYLON

JETT

SELECT

CENTERLINE
STA JETT SWITCH

JETTISON CONTROLS J—
-- /f-4C

FRONT COCKPIT

Figure 1-8

ECM pod. ECM pods on 2 , 5, and 8 are jettisoned by
following the normal jettison procedures for those
stations. The ECM pod on station 9 is jettisoned by
placing the wing tank jettison switch to JETT. After
T.O. 1F-4-863, the OUTBD pylon jettison selector
(figure 1-8) may be positioned to individually jettison
the contents of either outboard station. ECM pods on
stations 4 and 6 cannot be jettisoned^

Note

Any decision to jettison ECM pods must be
left to the appropriate command authority.

MISSILE JETTISON (INBOARD WING AND FUSELAGE
STATIONS)

The jettison circuitry within the firing circuits is
controlled by the missile jettison knob on the missile
status panel. The AC may manually select any one of I
the fuselage missiles or either of the inboard wing I
stations for jettison. AIM-7 missiles cannot be load- |
ed or launched from the inboard armament pylons.

The AIM-9 missiles can be jettisoned from the in¬
board missile launcher, When missile jettison knob
is positioned to either the L-Wing or R-Wing and the
center push to jett button is pushed, the AIM-9
missiles at the selected station are launched unguid¬
ed. The inboard armament pylon cannot be jettisoned.
The AIM-9 missiles can be jettisoned only when the
wing flaps switch is in the UP position.

When the missile jettison knob is pushed to jettison I
the fuselage stations, the ejection squibs are acti¬
vated any time EXT or GEN power is on the aircraft.
The ejectors used to launch the fuselage missiles are
activated by jettison voltage and not the fire voltage.
These ejectors are gas cartridges which explode to
eject the missile downward from the fuselage. The
jettison circuitry for the two forward fuselage mis¬
siles is interlocked in such a manner that, if the TK
light is illuminated, the missiles cannot be jettisoned.
The AIM-7 missiles are jettisoned without motor ig¬
nition.

Note

After T.O. 1F-4-750, the TK light will be on
before and after the Ml 18 or MK 84 bomb is
released when the centerline single bomb
shorting plug is installed. Even though the
TK light is on, the tank aboard relay is not
energized, permitting the two forward AIM-7
missiles to be monitored, launched, and jet¬
tisoned.

SUSPENSION EQUIPMENT (F-4C)

CONVENTIONAL WEAPON SUSPENSION

The suspension equipment used for carrying all forms
of conventional weapons is shown in figure 1-9. The
weapons carriage capability of the aircraft may be
summarized as follows:

a. The centerline (CL) station BRU-5/A (AERO-
27/A) rack, which receives

(1) A single weapon; or

(2) A CL weapons adapter, which receives either
the gun pod or the MER (six station carrier)
for multiple weapons carriage.

b. The left and right inboard wing (LI, RI) arma¬
ment pylons which receive

(1) A single weapon; or

(2) The LAU-34/A launcher for AGM weapons; or

(3) The TER (three station carrier) for multiple
weapons suspension.

c. The left and right outboard wing (LO, RO) arma¬
ment pylons which receive

(1) A single weapon; or

(2) The LAU-34/A launcher for AGM weapons; or

(3) The MER (six station carrier) for multiple
weapons suspension.

Air-to-air missile suspension equipment is described
in later paragraphs. Special weapon carriage meth¬
ods are described in T.O. 1F-4C-25-1.

Change 6

1-21

T.O. 1F-4C-34-1-1

“ . . ;

SUSPENSION EQ UIPMENT IgH HE

HOMING SAFET
LIGHT FIN

HOMIN'

TER-9

MER-U

U SAFETY PIN

4815973-1 (DOUGLAS)
TWO SAFETY PINS REQUIRED
FOR EACH MER/TER
EJECTOR RACK.

TER-9A

MER-10A

(Automatic

Homing)

SAFETY PIN (ELECTRICAL

4815967-1 (DOUGLAS)

ONE SAFETY PIN REQUIRED
K# IN EACH MER/TER RACK.

F4C-34-L123-1

Figure 1-9 (Sheet 1 of 4)

1-22

Change 2

CAUTION ^

l» MU 5HA»T *5
iVISIWJ UK*AO*

I 15 UNLATCHED

OtOUND SAfUV
FIN HOU

WITHOUT CARTRIDGES

CAUTION

* RtO 5MAH 15
VtSWUC UMKA&5
15 UNtAKHIO

WITH CARTRIDGES

F4C-34-I-123-2

Figure 1-9 (Sheet 2 of 4)

T.O. 1F-4C-34-1-1

OUTBOARD ARMAMENT PYLON

F-4C

SUSPENSION EQUIPMENT

> a

CENTERLINE

NORMAL FORWARD SUSPENSION

MER SHIFTED AFT

4C-34—1 — 1-(12-4)

Figure 1-9 (Sheet 4 of 4)

T.O. 1F-4C-34-1-1

BRU-5/A BOMB RACK (AERO 27/A )
BEFORE T.O. 1F-4-750

The BRU-5/A bomb rack (figure 1-9, sheet 3) is a
self-contained ejector unit mounted within the air¬
craft at centerline station 5. The Aero-27/Arack has
four suspension hooks: two 14 inches apart and two 30
inches apart. The BRU-5/A rack has only 30-inch
hooks and arming solenoids in place of the 14-inch
hooks. An ejector piston is in the center of the rack.
Operation of the rack hooks and the ejector piston is
initiated through the jettison circuit or the nuclear re¬
lease circuit by igniting two ejector cartridges.

Gases from the ejector cartridges cause the rack
hooks to open and the ejector piston to push down¬
ward on the bomb or suspension equipment. An
electrical safe switch is opened, when the bomb rack
safety pin is installed, to prevent the cartridges
from firing; the pin is removed prior to flight. The
MER cannot be suspended from the bomb rack with¬
out the centerline bomb rack adapter. The weight of
the Aero 27/A bomb rack (51 pounds) is not included
in the basic weight of the aircraft and must be in¬
cluded in any gross weight computation. The weight
of the BRU-5/A is 45 pounds.

After T.O. 1F-4-750, the two 14-inch suspension
hooks are replaced by two arming solenoids. A cen¬
terline single bomb shorting plug is installed to per¬
mit the release of the MK 84 or M118GP bomb
through the conventional release circuit. Illumina¬
tion of the TK light reveals the installation of the
shorting plug.

Note

Even though the TK light is on, the tank
aboard relay is not energized; therefore, the
forward AIM-7 missiles can be monitored,
launched, and jettisoned.

After the bomb is released, the TK light remains on.
The M118 or MK 84 on centerline can be jettisoned
with the external stores jettison button, the center-
line tank jettison switch, the nuclear store jettison
switch, and can be released through the DCU-94/A
control monitor.

CENTERLINE BOMB RACK ADAPTER

The centerline bomb rack adapter (figure 1-9,
sheet 3) is attached to the centerline position to ac¬
cept the MER assembly. The adapter is compatible
only at the centerline, and attaches directly to the
BRU-5/A bomb rack. The adapter weighs 55 pounds.

MAU-12B/A ARMAMENT PYLONS

The inboard and outboard armament pylons (figure
1-9, sheets 1 and 2) are bolted to the wing at sta¬
tions 1, 2, 8, and 9. The pylons cannot be jettisoned.
Each armament pylon assembly includes the MAU-
12B/A ejector rack, weapons relay panel, a power
rectifier, and bomb release circuits. The ejector
rack contains two cartridge breeches and ejector
pistons, 14 and 30-inch suspension hooks, three
arming wire solenoids, and a solenoid operated as¬

sembly that electrically locks (safeties) the cartridge
fire circuit. When the cartridges detonate, gas
pressure opens the rack hooks and forces the pistons
downward, ejecting the bomb. To compensate for
various bomb CG locations, orifices are installed
into the rack to control bomb separation character¬
istics by varying the forces delivered to the piston.
The ground safety pin when installed - provides only
a mechanical lock in the hook linkage for ground
safety purposes. The inflight safety lockout solenoid
electrically isolates the cartridges by mechanically
controlling two switches that break the cartridge
circuit. The lock must be removed when the MER or
TER is aboard by manually installing the flight
safety lockout pin (or bolt) in the pylon. The bolt is
installed only for non-nuclear bomb carriage and
must be removed for nuclear carriage. When the
bolt is installed, the DCU-94/A Unlock light for that
station illuminates continuously. The arming wire
solenoids are controlled by the position of the arm
nose tail switch.

Note

The MAU-12C/A is completely interchange¬
able with the MAU-12B/A armament bomb
rack. The MAU-12C/A is a strengthened
MAU-12B/A.

LAU-34/A LAUNCHER

This assembly must be used to carry and launch the
AGM-12B and AGM-45A missiles. The launcher
contains the electrical circuits and relays which are
responsible for the dispersal of missile pre-heat,
pre-arm, and missile launch voltage. The method of
carriage is illustrated (figure 1-9). The launcher
also contains a cartridge-fired jettison gun assembly.
Expanding gas from the detonated cartridges oper¬
ates the assembly and slides the missile rearward,
free of the launcher rails. The missile freefalls in
an inert state.

MULTIPLE EJECTOR RACK (MER)

The multiple ejector rack used at the outboard wing
stations and the centerline station are the MER-10
and MER-10A. The MER-10A function differs from
the MER-10 as follows:

a. Only the loaded MER-10A stations receive a re¬
lease pulse regardless of the arm nose tail switch
position.

b. The MER-10A is automatically homed to the first
loaded station in sequence each time power (28vdc
ESS BUS) is applied to the aircraft. The MER-10A
does not have a homing light.

c. The step switch on the MER-1QA is used for
ground checkout operation.

The MER has two suspension lugs mounted 30 inches
apart. The MER consists of six 14-inch ejector
units, 12 arming solenoids, the control unit and
wire bundles required to arm,release .and/or fire
munitions carried. Each ejector rack or point is
identified with a number corresponding to its re¬
lease sequence. All MERs are rigged 1° nose down
for rockets. The centerline MER weight is 215
pounds; the outboard MER weighs 225 pounds.

1-26

Change 5

T.O. 1F-4C-34-1-1

TRIPLE EJECTOR RACK (TER)

The triple ejector racks used at the inboard wing
stations are the TER-9 and TER-9A. The TER-9A
function differs from the TER-9 as follows:

a. The TER-9A is automatically homed to the first
loaded station in sequence each time power (28vdc
ESS BUS) is applied to the aircraft. The TER-9A
does not have a homing light.

b. The step switch on the TER-9A is used for
ground checkout operation.

c. Only the loaded TER-9A stations receive a re¬
lease pulse regardless of the arm nose tail switch
position.

The TER has two suspension lugs mounted 30 inches
apart. It consits of three 14-inch ejector units, six
arming solenoids, control unit and wire bundles re¬
quired to arm, release, and/or fire munitions that
are carried. Each ejector rack or point is identified
with a number corresponding to its release sequence.
TER's are permanently rigged 1° nose down. The
TER weighs 95 pounds.

REHOMING MERS AND TERS

A hung bomb can be released, in some cases, after
rehoming the MERs and TERs. Rehoming is accom¬
plished in flight by cycling the weapon selector knob
from BOMBS to RKTS & DISP and back to BOMBS.
This action causes the station stepper switch in all
MER/TERs aboard to move from the OFF position
to the first loaded station in sequence. The stepper
switch will not move if on a loaded station or the
MER/TER is empty. (A defective store aboard sen¬
sing switch could cause the MER/TER to appear emp¬
ty.) The MER/TER stepper switch OFF position is
obtained only in the BOMBS mode and after a release
pulse has been sent to each of the loaded stations on
the MER or TER. Additional bomb release pulses
will not move the stepper switch from the OFF posi¬
tion. Selecting RKTS & DISP moves the stepper
switch from the OFF position because there is no
OFF position in the MER/TER with the RKTS & DISP
mode. The MER/TER stepper switch always steps
to the next loaded station and continues to repeat the
cycle when the RKTS & DISP mode is used.

Note

Do not confuse the rehoming procedure per¬
formed by the aircrew with the homing pro¬
cedure performed by the load crew. The
load crew will position the STEP-OFF-
HOMING switch on the MER-10 or TER-9 to
HOME and obtain a steady green light. (The
TER-9A and MER-10A do not have the green
homing light nor the homing switch. The
rack automatically homes to the first loaded
station in sequence each time power, 28vdc
Essential Bus, is applied.)

The following causes of bomb release failure can be
corrected in flight by rehoming the MER and TER,
provided the MER/TER stepper has arrived at the
OFF position.

a. Improper homing of the MER or TER on the
ground.

b. Moisture in the bomb ejector rack breech that
grounds-out the release signal. After the MER and

TER are rehomed, succeeding release pulses can
(in come cases) generate sufficient heat to evaporate
the moisture in the bomb ejector rack breech.

The following causes for failure of the bomb release
circuit cannot be corrected inflight by rehoming the
MER and TER:

a. Faulty ejector rack cartridges.

b. Broken or shorted wiring to the ejector rack
cartridges.

c. Faulty relays.

If all the bombs carried will not release, the ejector
racks should be rehomed and release attempted
again. Rehome the MER and TER as follows:

a. Weapons selector knob - RKTS & DISP

After the remaining switches are set for bomb re¬
lease, the bomb release button is depressed and held
for 4 seconds with BOMBS/RIPPLE selected. With
the MER-10/TER-9, if the weapon will not release
when the arm nose tail switch is in an armed posi¬
tion, rehome and then repeat the BOMBS/RIPPLE
release procedure with the arm nose tail switch in
SAFE. If the station loaded sensor switch is failed
in the station empty position, releasing the weapons
safe supplies a release pulse to the loaded stations
and the unloaded station.

Note

• The arm nose tail switch position does not
affect the operation of the TER-9A, MER-
10A stepper switch; the release pulse is
directed only to the loaded stations.

• If the bombs cannot be released after per¬
forming the preceding procedures, it must
be assumed that the ejector rack cartridges
will not fire, or the MER or TER is mal¬
functioning.

Consider the situation where three x'ocket launchers
are loaded on a TER. The TER stepper switch has
four positions: 1, 2, 3, and OFF. The first loaded
point in sequence is referred to as the home position.
Assume that the rocket launchers on points one and
two have been fired-out and the rocket launcher on
point three is full, i.e., no attempt was made to fire
the remaining rocket launcher. (The full launcher
must be released or fired before the empty launchers
can be released.) To release the rocket launcher,
the weapon selector knob is positioned to BOMBS.
When the bomb release button is depressed, a pulse
is supplied to release the full rocket launcher on
point No. 3. When the bomb button is released, or
the firing pulse is ended, the stepper switch moves
to OFF. Succeeding pulses will not move stepper
switch from OFF. To release the two remaining
empty launchers, the weapons selector knob must be
positioned to RKTS & DISP. Power is now supplied
to the stepper switch to position it to a loaded point;
in this case, point No. 1. The AC can now select
BOMBS and release the two empty dispensers.

In this example, the rocket pods are released from
the TER out of normal bomb release sequence, i.e.
TER station 3, 1, 2. The normal bomb release se¬
quence is TER station 1, 2, 3 (refer to figure 1-7).

Change 8

1-27

T.O. 1F-4C-34-1-1

AERO-7A MISSILE LAUNCHER

1 AIM-7 MISSilT

AERO-TA LAUNCHER
SAFETY PIN (4)

4C—34—1 — 1—(13)

Figure 1-10

Rocket pods and CBU dispensers (full and
empty) should be released from the MER/

TER in the normal bomb release sequence
to avoid possible aircraft damage.

There is presently no cockpit indication or procedure
to ensure which MER/TER station is selected for
BOMBS release after RKTS & DISP has been used.
The position of the MER/TER stepper switch is es¬
tablished by the number of dispensing signals to the
aircraft station and the number of dispensers (or
rocket pods) on that station; i.e., the number of dis¬
pensing pickle signals to a loaded station must be
equal to tire number of dispensers loaded on that
station (or a multiple of the number of dispensers on

that station) prior to selecting BOMBS to release
the dispensers/rocket pods from tire MER/TER.

AERO-7A MISSILE LAUNCHER
(AIM-7D/E/E-2) MISSILE

Four Aero 7A launchers are mounted in the fuselage
so that four AIM-7D/E missiles are semi-submerged.
The Aero-7A launcher (figure 1-10) has two ejector
pistons which are operated by gas generating car¬
tridges to eject the missile downward approximately
8 inches before the missile motor is fired. Each of
the forward fuselage stations has a cavity door that
closes after the missile is gone, to smooth the con¬
tour of the fuselage. Each launcher is electrically
and mechanically protected from inadvertent firing
of the ejector cartridges by a safety pin which is re¬
moved prior to flight.

1-28

Change 4

LAU-7A/A MISSILE LAUNCHER

| Refer to T.O. 1F-4C-34-1-1A.

T.O. 1F-4C-34-1-1

AGM-12 WEAPON SYSTEM (F-4C)

This section describes the AGM-12B/C/E guided
missile launching system and, cockpit controls and
controlling procedures. Refer to part 4 of this sec¬
tion for a description of the AGM missiles.

With respect to missile control and flight operations,
the missiles are nearly identical. The AGM-12B and
12C missiles are both ground burst devices, with the
AGM-12C being considerably greater in weight and
explosive yield. The AGM-12E is basically the same
as the AGM-12C, except the -12E missile is an air-
burst, anti-personnel device.

MISSION DESCRIPTION

The AGM-12 missile and associated equipment pro¬
vides the radio-controlled guided missile capability
to enhance the air-to-ground strike mission. With
the AGM-12 system energized, the AC begins an at¬
tack (dive or level) on the target and stabilizes the
airplane flight path directly toward the target. The
AC attempts to maintain a constant line-of-sight
(LOS) with the target throughout the missile run. The
missile fire signal is delivered by depressing the
bomb button (either cockpit), igniting the missile
liquid-fuel engine and the tracking flares. After en¬
gine burn-out (approximately 2.0 seconds) the AC
begins transmitting steering commands to the mis¬
sile receiver. The system transmitter emits ther-f
signals as the control selector handle is positioned
in combinations of left-right or up-down movements.
Hence, the AC directs the missile flight path in azi¬
muth and elevation, causing the missile (visible
tracking flares) to close on the LOS to the target.

CONFIGURATION AND SUSPENSION

AGM-12B MISSILE

Four AGM-12B missiles, one on each wing station
may be carried and launched against ground targets.
The suspension system is shown in figure 1-9. The
LAU-34/A launcher is loaded directly on the arma¬
ment pylon bomb rack. The branched wire bundle
from the armament pylon is attached to both recep¬
tacles on the aft end of the launcher. The forward
branch powers AGM-12B functions; the aft branch
powers AGM-45 missile functions which are dis¬
cussed later in this section. In a jettison situation,
only the missile is jettisoned; the launcher remains
on the aircraft.

AGM-12C AND -12E MISSILES

A total of two AGM-12C and -12E missiles may be
carried, one on each inboard station. An AGM-12
relay panel, installed only in the inboard armament
pylon, relays the pre-arm and missile fire/release
signals from the cockpit. Hence, the missile is
loaded directly on the pylon (MAU-12B/A) bomb
rack. In this case, the fire signal ejects the missile
from the rack and the missile engine ignites immedi¬
ately after ejection. A discussion of AGM-12C/E
missile fire and jettison procedures is provided later
in this section.

LAU-34/A LAUNCHER (AGM-12B CARRIAGE)

The launcher (figure 1-9) is responsible for the
proper dispersal of pre-heat, pre-arm, and missile
fire voltage. When the aircraft main bus system is
energized, power is automatically directed to mis¬
sile components for warm-up purposes and the sys¬
tem transmitter receives standby power. Thus, the
system is in a warm-up condition as soon as the
main bus system is energized.

When the AC selects the AGM-12 missile on the
weapon selector switch, relays in the launcher are
energized that unlock the pre-arm and missile fire
circuit. As the AC depresses (and holds) the bomb
button, the missile battery, gyro, pneumatic control
system, and warhead arming circuits are activated.
The missile battery builds up to power and closes a
relay in the launcher — completing the circuit be¬
tween the bomb button (depressed) and the liquid en¬
gine ignitor. The firing sequence takes approxi¬
mately 2 seconds. The engine thrust force breaks the
shear pin in the forward retention mechanism and the
missile is free to launch. As the missile separates
from the aircraft, the umbilical breakaway connec¬
tor separates and the missile systems function on
battery power.

If the AGM-12B must be jettisoned, the jettison sig¬
nal energizes a cartridge in the launcher jettison gun
assembly. The force of the expanding gas from the
cartridge rotates the aft retention mechanism and
slides the missile rearward, free of the launcher
rail. In this case, the missile freefalls in an inert
state. Only under the condition of a normal, powered
launch will the warhead become armed.

Change 2

1-29

T.O. 1F-4C-34-1-1

. ._

CONTROL HANDLE vs. CANARD DEE LECTION

T (Time)

F4C- 34-1*125

Figure 1-11

AIRCRAFT COMPONENTS

TRANSMITTER AND CONTROL SELECTOR
(AN/ARW-77)

With the aircraft bus system energized, 28 volt dc
power is continually applied to the transmitter elec¬
tron tube filaments, crystal heaters, and voltage
regulator. When bomb button voltage is applied at
launch, the ARW-77 transmitter signal is initiated
and an internal timer (in the transmitter) begins a
50 ± 10 second cycle. The timer sustains transmit¬
ter output for the above time period after the AC re¬
leases the bomb button. The output signals from the
cockpit control selector are converted into command
pulses by the transmitter. The transmitter circuits
code, amplify, and apply the commands to the lower
UHF antenna. Any one of the 24 command channels
may be used, depending upon the crystal installed in
the transmitter. The transmitter crystal assembly
installed must match that of the missile receiver.

The control selector (figure 1-12) receives power
directly from the transmitter and in turn applies
command output voltages to the transmitter circuit.
With the control handle in the neutral position, the
system continually emits a neutral or reference sig¬
nal. Movement of the handle causes signal changes
with respect to the reference signal. The amount of

change is directly proportional to handle displace¬
ment. A further discussion of control handle func¬
tions in the command link system is provided in later
paragraphs. Transmitter output to the missile is
always emitted through the lower UHF antenna on the
nose gear door. Any UHF radio transmission, while
the AN/ARW-77 transmitter is in operation, is auto¬
matically emitted through the upper UHF antenna,
regardless of the antenna switch position (UPR or
LWR).

MISSILE CONTROL

ADAPTIVE CONTROL SYSTEM

The features of the adaptive control system may be
described by observing the functions of an individual
command. These functions (listed below) are directly
controlled by AC manipulation of the control handle
in the cockpit:

a. Lead Pulse.

b. Variable Pulse Rate Frequency.

c. Auto-Check Command.

d. Memory Command.

When the AC deflects the control handle providing an
input voltage to the transmitter, circuits in the trans¬
mitter develop command pulses by repeatedly conduct-

1-30

T.O. 1F-4C-34-1-1

AGM-12 CONTROL SELECTOR^_,

- - j±4£]

F4C-34-I-126

Figure 1-12

ing and deenergizing, applying and removing voltage
for transmitter pulse output. The net result is that
the missile canards momentarily deflect and then re¬
turn to neutral as each pulse is applied, continuing
the pulsating deflections as long as the handle is dis¬
placed. The canards always deflect fully with each
pulse, regardless of the degree of control handle dis¬
placement. As an example, assume that the AC —
having launched a missile — applies an up correction
by moving the handle aft. Further, assume that the
stick is deflected about one-half travel at time To,
and then returned to neutral at time Tj (figure 1-11).
In the figure, off time refers to the time between
pulses when the canards are neutral: on time refers
to pulse duration, which corresponds to canard de¬
flection time.

Since an up correction is necessary, the missile is
low with respect to the LOS and probably going lower
due to the effect of gravity. (Also, note that the AGM-
12C missile is ejected and not launched, which ap¬
plies another force component to the missile normal
to the LOS.) Hence, as the AC moves the stick, the
command must initially apply enough energy to rotate
the missile axis and change its course, and in some
measure account for the time lag in the command
link system. The lead pulse, that functions to quicken
missile response for the above reasons, is applied
for a longer period than subsequent pulses as figure
1-11 indicates. The width, or on time, of the lead
pulse is proportional to how rapidly the AC moves (or
accelerates) the stick to the desired position. A rapid
movement delivers a lead pulse of greater duration
than that of a gradual movement. This is in keeping
with the natural tendency to correct rapidly if the AC
notices a large error developing. Conversely, the
lead pulse function points out the necessity of using
gradual, smooth, control stick movements in in¬
stances where missile steering is extremely sensitive
or where steering errors are small.

As long as the control handle is held in the deflected
position, the pulse train continues. After the lead
pulse, subsequent pulses are short at first, increas¬

ing in duration (time) as the stick is held. This
means that the canards are deflected for increasing
periods of time with each pulse. If the AC increases
the amount of handle deflection, the amount of pulses
per unit of time increases, or in other words, the
frequency increases. Hence, the pulse rate frequency
varies proportionally with the amount of handle dis¬
placement. If the handle is displaced to full travel,
the pulse is continuous and canard deflection is con¬
tinuous. This is the same as stating (regarding figure
1-11) that off time decreases and on time increases
as handle displacement increases. The idea is that
the AC deflects the handle a specific amount for an
observed error. Then as the missile is observed to
correct toward LOS at a satisfactory rate, handle de¬
flection may be reduced so that the amount of error
and command pulses delivered approach a condition
of balance. Small random errors are then corrected
by slight, smooth handle movement about the neutral
position.

As the handle is returned to neutral at time Tl, the
automatic check command is delivered. The check
pulse performs very nearly the same function as the
lead pulse, but the situation is reversed. As the mis¬
sile corrects and approaches the LOS, a force must
be applied to rotate and align the missile axis with
the LOS - preventing overshoot. Just as the lead
pulse, the pulse duration of the check command is
proportional to the rate of handle movement to neu¬
tral. If the AC notices an overly rapid rate of clo¬
sure with the LOS, he would naturally return the han¬
dle to neutral at a rapid rate. Thus, the AC is able
to reduce lateral or vertical acceleration without
handle deflection in the opposite direction.

After control handle voltage is removed, the system
automatically generates small memory commands at
a constant rate. These commands will continue
throughout missile flight time unless they are coun¬
tered by stick movement in the opposite direction.

The frequency of the memory commands is a func¬
tion of the amount and duration of the initial handle
displacement. A small handle deflection held for a
long duration can develop the same memory as a
large handle deflection held for a short duration. The
memory circuits function to aid in overcoming natural
forces continually acting on the missile. In the ex¬
ample command cited here, the up memory would
serve to compensate for further gravity drop.

In view of the above, one can visualize the system
when handle movements are made in directions other
than the cardinal ones. If the handle is moved to de¬
liver an up-right command for example, the com¬
mand sequence in figure 1-11 is applied in both up
and right directions simultaneously. The point to be
made is that the AC need not restrict control move¬
ment to cardinal directions only, but may use com¬
binations of the cardinal commands and vary their
magnitude.

CONTROL CONSIDERATIONS

The above discussion treats the system somewhat
ideally for purposes of demonstration. In practice,
there are several more things to consider. The AC

1-31

T.O. 1F-4C-34-1-1

must establish the desired LOS with the wings level,
applying enough forward trim to counteract the ten¬
dency for the nose of the aircraft to rotate as velocity
during the dive increases. Remember that the mis¬
sile gyro is uncaged while the missile is still on the
launcher, and that the gyro establishes a vertical ref¬
erence relative to the position of the aircraft. Thus,
if the aircraft is in a 45° left bank at launch and sub¬
sequently rolled level after launch, an up-command
will result in the missile steering up-left.

When firing the liquid engine, the missile will be
plainly visible at launch. Engine burnout is identified
by a puff of white smoke. The AC must ensure no
commands are issued until after engine burnout. The
AC will obtain best results if he can avoid the natural
tendency to fix his vision on the missile flares after
launch. Rather, keep the eyes fixed on the target (or
impact point on the target) and view the missile flares
through the peripheral vision. The picture is similar
to the pipper light floating on the wind screen. This
procedure will help maintain a steady LOS.

In most cases, the missile appears below the target
and to the left or right, depending upon the wing sta¬
tion used. If the missile is low, the first feasible
command is the up command to initiate the upward
correction, and to help counteract further sink due
to gravity by establishing up memory. At the lower
release angles, the effect of gravity will be greater.

If the missile is initially high before any commands
are issued, allow gravity to correct the elevation
error. A down command with down memory, plus
the effect of gravity, is sure to result in overshoot
below the LOS. With all systems functioning nor¬
mally, the command link system is most sensitive
during the first few seconds after engine burnout.
Hence, use smooth control action to establish a de¬
sirable corrective trend toward LOS, rather than
attempting to eliminate all sources of error im¬
mediately. Missile steering tendencies will vary;
that is, some missiles will be more sensitive than
others. When applying the initial command, how¬
ever, all missiles shouldbe regarded as very sensitive;
it is easier to add more handle displacement than to
correct an over-controlled missile.

The AC can get an idea of how much handle deflection
is needed by observing missile trend. To illustrate,
suppose the flares are observed to move from left to
right toward the LOS at a rapid rate. At the instant
the flares move into and coincide with the LOS, the
apparent error is zero; but the error trend remains
very large since the angle between the missile axis
(or flight path) and the LOS is relatively large. In
this case, considerable control movement, with
proper lead, would be necessary to avoid overshoot.
However, if the missile is considerably wide but gen¬
erally holding position relative to the LOS, the mis¬
sile axis may be considered to be nearly parallel to
the LOS. In this case, a lesser control deflection is
necessary to divert the missile and the AC uses
smooth control input, varying handle deflection only
to establish a controllable correction rate.

If the missile can be established at a point close
(and parallel) to the LOS early in flight, there should

never be any need for large, rapid, control handle
movements. In fact, during the early phase of mis¬
sile flight, the AC will usually have to use conscious
effort to avoid overcontrol. With the adaptive sys¬
tem, a small degree of handle displacement held for
a longer time produces the same effect as a full de¬
flection for a very short interval. The former is by
far the more desirable, however, since the trend of
missile correction is more easily judged. The con¬
tinuing effect of gravity must be kept in mind, and
possibly used to an advantage. As dive angle in¬
creases, that component of gravity that tends to pull
the missile down from the LOS becomes less. How¬
ever, if the missile steers slightly high, up memory
will probably not be sufficient to continually hold the
missile high and gravity may be used to make the
necessary correction. The AC must avoid anticipat¬
ing the impact, and continually fly the missile until
impact is observed.

Roll Reference Shift

The description of the AGM-12 gyro system (part 4)
points out that at supersonic velocity, the missile
roU rate is an average 500° per second. Further,
the pickoff brushes in the missile gyro are biased 50“
to compensate for 0.1 second time lag in the com¬
mand link system. As the missile decelerates, how¬
ever, and approaches the transonic region (Mach 1.1
to 0.9), the lift force at the bent wing tips increases
rapidly and causes a rapid increase in roll rate.
Missile roll can increase to an approximate maxi¬
mum rate of 1000 1 per second. Thus, maximum shift
becomes approximately 100°, which means that the
original 50° bias no longer compensates for the com¬
mand lag and missile response would occur 50" coun¬
terclockwise from the desired response. It is diffi¬
cult to predict the point at which roll reference shift
begins since one must consider factors such as
launch angle, launch velocity, and individual control
technique which directly effects the rate of missile
deceleration. If the technique of steering the mis¬
sile along the LOS is executed properly, the buildup
rate of roll reference is very slow and actual ob¬
servance of the shift phenomenon is impossible.

A rule-of-thumb method has been devised that —
knowing a desired time of flight (Tf)—may be used
to determine launch altitude (AGL) for a specific
dive angle. The method makes use of a factor which
corresponds to a specific Tf as follows:

Factor

0.3

10 sec.

0.4

15 sec.

0.5

20 sec.

0.6

25 sec.

0.7

30 sec.

For example, assume the AC begins the dive on tar¬
get, establishes LOS, and observes the dive angle to
be 35°. If the 20 sec. Tf is planned, the factor of
0.5 is applied (above) so that launch altitude (AGL)
is:

0.5 x 35° dive = 17.5 thousand feet AGL.

1-32

T.O. 1F-4C-34-1-1

If target altitude is 1500 feet MSL, indicated launch
altitude becomes:

17.5 +1.5 = 19.0 thousand feet.

The above method is accurate within ± 2 seconds for
dive angles within 15° and 45°, and launch airspeeds
between 300 and 600 KTAS.

Offset Deliveries

All previous considerations stated apply to offset
deliveries. In this delivery, the LOS continually ro¬
tates. For example, if the target is approximately
10° right at launch, it may move to a relative posi¬
tion of 40° right at impact. In view of the shift phe¬
nomenon discussed above, the target must always be
offset to the right. In a shift environment, a right
command would result in an up-right response, a
relatively easy situation to control. A left command,
however, would result in a down-left response, which
is nearly impossible to control in an offset mode. In
any delivery situation, the rate of LOS rotation can
be reduced by reducing airspeed to as low a rate as
the situation permits.

COCKPIT CONTROLS

As mentioned previously, AGM-12 selection and fire
procedures are nearly identical. The AGM-12C and
-12E missiles may be carried only on the armament
pylon (inboard station). The AGM-12B may be
launched from either pylon configuration since the
LAU-34/A launcher must be used. Hence, in these
aircraft, the same switches are used to select and
fire either missile. It is only necessary to point out
minor differences in the firing sequence for the mis¬
siles.

AGM-12 SELECTION

Since power is immediately available to warmup sys¬
tem components, there is no need to position switches
for this purpose. With the main bus system ener¬
gized, power is available for missile components re¬
quiring preheat and for the system transmitter in the
aircraft. The AC arms the AGM-12 firing system by
positioning switches on the multiple weapons control
panel (figure 1-6).

Weapon Selector Knob

AGM-12B. With the weapon selector (WPN SEL)
knob positioned to GAM-83 (AGM-12), the AC arms
the following circuits: (1) Two launcher relays are
energized: one closes the circuit which allows bomb
button voltage to activate the missile thermal battery
and arming circuits at fire time. The other closes
an interlock in the bomb button/missile igniter cir¬
cuit. (2) The selection also energizes the GAM-83
relay, which will direct bomb button power (through
the Gam - Aux switch) to activate the transmitter
timer. The bomb button signal actually energizes a
timer in the transmitter, which sustains transmitter
output for 50 ± 10 seconds. The functions of condi¬
tion (1) above cannot go further until the AC ener¬
gizes the switches discussed below.

Only the GAM-83 position may be selected to
launch the AGM-12 missile. However, this
position also energizes the release circuit
and release whatever bomb might be loaded
on a selected ordinance station MER or TER.
Hence, selecting GAM-83 — with loaded MER
or TER equipment aboard — is the same as
selecting BOMBS SINGLE.

AGM-12C/E. The same functions, as stated above,
also apply to the AGM-12C and -12E missiles. The
only difference is that the weapon selector switch
closes circuits (comparable to statement 1 above) in
the AGM-12C relay panel in the inboard armament
pylon.

Master Arm Switch

The master arm switch unlocks the non-nuclear
weapons release circuit and powers the station se¬
lector knob. The ARM position energizes the bomb
button transfer relay, which must be energized to
fire the AGM-12 missile. Power for the transfer re¬
lay passes through contacts of the special weapons
relays, which means that the special weapon release
circuit must be deenergized to fire non-nuclear weap¬
ons. This condition is satisfied if any of the follow¬
ing controls are OFF; the DCU-94/A master release
lock switch, the nuclear consent switch, or the five
station selector switches. The SAFE position of the
master arm switch deenergizes the bomb button cir¬
cuit and drops power from the station selector knob.

With the transfer relay energized, depressing either
bomb button directs voltage to the intervalometer.

The intervalometer returns a single firing pulse -
alternately to the left or right missile station. The
firing pulse passes through the inboard or outboard
launcher relays, which are controlled by the station
select knob.

Station Selector Knob

With the master arm switch in ARM, 28 volt dc power
is available for the station selector. Selecting the
INBD or OUTBD WING positions closes the inboard
or outboard station relays, respectively. The relays,
which form the last interlock in the missile-fire cir¬
cuit, must be closed to get each fire pulse from the
intervalometer to the missile station. With the
AGM-12C aboard, only the INBD position would ap¬
ply.

Intervalometer Step Switch

The step switch is used to electrically reset the in¬
tervalometer. Operating power for the intervalom¬
eter flows through the NORM position of the switch.
Selecting the RESET position drops power from the
intervalometer, causing the reset condition. This as¬
sures that the next (or first) missile-fire pulse is
applied to the left select wing station. The step
switch is spring-loaded to NORM.

1-33

T.O. 1F-4C-34-1-1

Note

Removing power from the intervalometer by
any manner, such as engine shut-down will
establish the reset condition.

The AC will usually fire left wing armament first. As
an example, suppose all four wing stations are loaded
and that the position of the fire (or release) pulse is
unknown. Further, suppose that one of the right wing
stations is to be fired first. Then proceed as follows:

1. Momentarily select RESET to get the launch
pulse to the left wing.

2. Place the master arm switch to ARM.

3. Place the weapon selector to BOMBS SINGLE.
(This will prevent ARW-77 timer operation
during step 5. The same thing can be accom¬
plished by holding the GAM-AUX switch to IN¬
TERRUPT during step 5).

4. Check that the station selector switch is OFF,
or else left wing armament will fire during the
next step.

5. Momentarily depress the bomb button; the in¬
tervalometer circuits will position so that the
next launch pulse will be directed to the right
selected station.

Now the AC selects a specific station (INBD or
OUTBD) to launch the AGM-12. If, during the above
procedure (step 5), the weapon selector is positioned
to GAM-83 (AGM-12), the transmitter timer will en¬
ergize for 50 ± 10 sec. This is of no consequence if
the AC accomplishes the above procedure at least 2
minutes prior to the actual launch; the timer will
run out and reset to a standby condition. However, if
the AC inadvertently energizes the ARW-77 timer,
and must launch the missile immediately, he may re¬
set the timer by momentarily positioning the Gam-
Aux switch to INTERRUPT prior to launch. The
INTERRUPT position should be held at least a second
or so to get a full (50 sec.) reset condition. The AC
must note that when the transmitter timer is reset in
this manner, the timer will not reset to a standby
condition. That is, when the INTERRUPT position is
released, the timer will begin again. One must allow
the timer to run out completely in order to get a
timer-standby condition. Hence, the net consequence
of not observing the above procedure is simply that
the ARW-77 timer may be partially run out at launch,
with the possibility that missile control may be lost
before impact.

Gam-Aux Switch

The functions of the Gam-Aux switch are generally
presented above. With power on the aircraft, 28 volt
dc standby power flows through the NORM position
to the transmitter. Momentarily selecting TEST en¬
ergizes the transmitter timer and initiates the r-f
signal output. The signal continues for approximately
50 seconds. The INTERRUPT position, which re¬
moves operating power from the transmitter, may be
used to guard against transmitting when the missile-
fire (bomb button) circuit is activated for any reason
other than missile firing. Also, the INTERRUPT po¬
sition will reset a partially expired timer as stated

immediately above. The AC might use the test func¬
tion in instances where a fly-by command link check is
desired with test equipment located on the ground.

The switch is spring-loaded to NORM.

Note

In some aircraft, the Gam-Aux switch may
not be spring-loaded. The AC must ensure
the switch is in the NORM position during
and after missile launch.

The Gam-Aux switch performs an additional function
for the AGM-12E missile. The INTERRUPT position
activates the Good Guidance Monitor (GGM) network,
a safety device in the missile fuzing system. (The
GGM function is described in T.O. 1F-4C-34-1-1A.)
To activate the GGM function during missile flight,
the INTERRUPT position must be held for at least
4 seconds.

Bomb Button

Power is available for the bomb button when the land¬
ing gear handle is placed in the UP position. With the
system switches positioned as specified above, de¬
pressing the bomb button starts the transmitter
timer and activates the thermal battery in the missile.
The bomb button must be held depressed until the
missile fires (approximately 2 seconds). The noise
of engine ignition, and possible airframe reactions at
launch, are plainly discernible to the aircrew.

AGM-12B. The bomb button signal initiates missile
thermal battery power, uncages the missile gyro,
and charges the pneumatic control system. As the
battery becomes active, battery power closes a relay
in the LAU-34/A launcher that completes the bomb
button/engine ignitor circuit, igniting the liquid en¬
gine. The entire sequence takes about 2 seconds.

AGM-12C/E. The functions stated above also occur
with the AGM-12C/E aboard. In this case, however,
the activated battery completes the bomb button/
ejector rack cartridge circuit and the missile is
ejected. Tension on the safety switch lanyard closes
the engine battery/igniter circuit and the engine ig¬
nites.

WARNING

In firing the AGM-12 missile, tests have
shown that certain quantities of missile ex¬
haust gas will enter into the cockpit area.

Since this gas is extremely lethal, the air¬
crew must ensure oxygen equipment fits
properly, and that missile firing operations
are conducted using 100% oxygen (both cock¬
pits) until the cockpit atmosphere can be com¬
pletely changed.

Note

Refer to part 4 of this section for a descrip¬
tion of the AGM missiles.

1-34

PART 2 DESCRIPTION

F-4D

TABLE OF CONTENTS

MISSION DESCRIPTION (F-4D)

Dive Bombing. 1-36

Direct Bomb Mode. 1-36

Rocket Launch. 1-36

Gun Firing. 1-36

Level Bombing. 1-38

Ripple Release Bombing. 1-38

Low Drag Bomb Delivery. 1-38

Fire Bomb Delivery. 1-38

CBU Delivery. 1-38

High Drag Bomb Delivery. 1-40

Leaflet Bomb Delivery. 1-40A

Flare Dispensing. 1-40A

Loft Bombing. 1-40A

AIRCRAFT WEAPON SYSTEM CONTROLS
(F-4D)

Delivery Mode Selector Panel. 1-42

Weapon Delivery Panel. 1-42

Station and Weapon Select Panel .... 1-42

Weapons Release Computer Set .... 1-52

Lead Computing Optical Sight. 1-56

Loft Bombing Equipment Controls . . . 1-59

WEAPON DELIVERY MODES (F-4D)

Air-to-Air Gunnery. 1-61

Direct Delivery Mode. 1-62

Dive Toss Bombing Mode. 1-64

Dive Laydown Bombing Mode. 1-68

Laydown Bombing Mode. 1-69

Offset Bombing Mode. 1-70

Target Finding Mode. 1-77

WRCS/LABS Delivery Mode. 1-77

FIRE CONTROL SYSTEM, AN/APQ-109,
-109A, -109(V)-4. Refer to T.O. 1F-
4C-34-1-1-1

JETTISON CONTROLS (F-4D)

Emergency Jettison. 1-80

Selective Jettison. 1-81

SUSPENSION EQUIPMENT (F-4D)

BRU-5/A (AERO-27/A) Bomb Rack. . . 1-83

MAU-12B/A, C/A Armament Pylons . . 1-84

Multiple Ejector Rack (MER). 1-84

Triple Ejector Rack (TER). 1-84

LAU-34/A Launcher. 1-84

Rehoming MER's and TER's. 1-84

Aero 7A Missile Launcher. 1-84

AIM-4D Missile Launcher. 1-89

AERO-3B Missile Launcher (Refer to
T.O. 1F-4C-34-1-1-1)

LAU-7A/A Missile Launcher (Refer to
T.O. 1F-4C-34-1-1-1)

AGM-12 WEAPON SYSTEM (F-4D)

Mission. 1-93

Configuration and Suspension. 1-93

Aircraft Components. 1-94

Missile Control. 1-94

Cockpit Controls. 1-97

AGM-45 WEAPON SYSTEM, Refer to T.O.
1F-4C-34-1-1-1

KMU-353A/B (MK 84 EO) GUIDED
WEAPON (Refer to T.O. 1F-4C-34-1-1-1)

LASER TARGET DESIGNATOR Refer to
T.O. 1F-4C-34-1-1-1

MARK 1 MOD 0 GUIDED WEAPON SYS¬
TEM, Refer to T.O. 1F-4C-34-1-1-1

RADAR HOMING AND WARNING SYSTEM
Refer to T.O. 1F-4C-34-1-1-2

T.O. 1F-4C-34-1-1

MISSION DESCRIPTION IF-4D)

DIVE BOMBING

Dive bombing with the F-4D aircraft can be per¬
formed with the aid of the weapons release computer
set, (WRCS), or by the DIRECT release mode with¬
out the aid of the WRCS. The WRCS delivery mode
normally associated with the dive bombing mission
is the DIVE TOSS bombing mode (figure 1-13). When
the DIVE TOSS bombing mode is used, the weapons
release computer solves the bomb ballistics problem
for various release speeds, altitudes, and dive angles
and automatically releases the bomb. Therefore,
mission planning is reduced to obtaining the drag co¬
efficient of the bomb and determining a safe recovery
altitude. Wind correction for the low drag bombs is
normally not required. Refer to wind correction.

Note

• Neutral rudder trim should be accomplished
at the planned delivery speed. Since the turn
and slip indicator in the rear cockpit is more
sensitive, the pilot should assist the AC by
calling the indicator display.

• The bombing tables in T.O. 1F-4C-34-1-2
assume normal G loading for the given dive
angle which can be obtained only when a
wings-level, straight line flight path is main¬
tained prior to release. The pipper should
be allowed to walk toward the target or aim-
point and should arrive when the aircraft is
at the release altitude and airspeed. The
roll tabs on the optical sight should be used
to maintain wings-level flight. If radar lockon
can be obtained, the range bar may be used

to establish the slant range.

DIRECT BOMB MODE

Several factors must be considered when determining
an indicated release altitude: altimeter position
error, altitude loss during pullout, minimum air¬
craft ground clearance; altimeter lag; and target ele¬
vation. The altimeter is set according to target
pressure reduced to sea level (target altimeter set¬
ting). Immediately following bomb release, a 4 G
pullout is initiated. The acceleration rate is 4 G ob¬
tained 2 seconds after release. If buffeting is en¬
countered, the buffet boundary is maintained until the
desired climb attitude is obtained. When the DIRECT
delivery mode (figure 1-13) is used, mission planning
becomes more detailed. The dive bombing tables
provide trajectory data for the various parameters
associated with the delivery. Consistency in the all-
important roll-in parameter cannot be overempha¬
sized. The parameters of altitude, airspeed, dis¬
tance from target, and power setting are preplanned
to place the aircraft at a predetermined release alti¬
tude and distance from target, with a predetermined
bomb release velocity and attitude to effect an accu¬

rate hit. Because of the longer periods of wind effect
on the trajectory of the bomb, it is also important
that the aircrew have knowledge of the magnitude of
wind effect and, primarily, the wind velocity at re¬
lease altitude.

Selecting the direct delivery mode enables the lead
computing optical sight to be used as a fixed sight
reference that can be depressed from zero mils to
245 mils below the fuselage reference line. The
actual sight setting is obtained by adding the F-4D
aircraft zero sightline angle of attack to the value
obtained in the bombing tables (T.O. 1F-4C-34-1-2).

The optical sight is used in conjunction with the al¬
timeter, and the calibrated airspeed indicator to de¬
termine the release point.

ROCKET LAUNCH

The DIRECT delivery mode is used to fire the 2.75
inch folding fin aircraft rocket (FFAR). The optical
sight is operated in the A/G mode. The sight depres¬
sion angles are presented in the rocket launch tables
as a function of angle of attack (gross weight) rather
than the depression angle from flight path. Only the
RKTS & DISP SINGLE position should be used when
firing the rocket launchers to ensure complete fire-
out of all rockets.

Note

If RKTS & DISP RIPPLE is selected, the
launcher will not fire-out completely be¬
cause the firing pulse directed from the air¬
craft intervalometer is not of sufficient
length to fire-out the launcher intervalom¬
eter.

Fuze arming is not a consideration for rocket launch
except when using the WDU-4/A Flechette Warhead,
refer to the confidential supplement for release con¬
siderations, section V. Safe escape considerations
are somewhat different in that the aircraft is flying
toward the frag envelope and possible secondary ex¬
plosions from the target. The safe escape tables in
section VI do not consider terrain avoidance nor
secondary target explosions. The effect of wind is
less than for bombs because of the shorter time of
flight. The rocket launch tables presented in T.O.
1F-4C-34-1-2 are valid for all rocket launchers and
type of suspension equipment used. Separate launch
tables are required for the various categories of
warhead used with the 2.75-inch rocket motor.

GUN FIRING

When firing the SUU-16/A gun pod in the air-to-
ground mode, either the OFF or DIRECT position
should be selected on the delivery mode selector
panel to orient the optical sight with the fuselage ref¬
erence line: refer to optical sight functions (figure

1-36

DIVE DELIVERY F-4D

LEVEL DELIVERY j F-4D / m

RELEASE ALTITUDE
START PULLOUT

ALTITUDE TLOST

RELEASE

ALTITUDE

MINIMUM ALTITUDE
AGL

HORIZONTAL RANGE

TARGET

Figure 1-13

BOMB RELEASE

RELEASE

ALTITUDE

BOMB RANGE

RELEASE PATTERN
OF ONE TUBE

RELEASE

ALTITUDE

TARGET

BOMB RANGE

Figure 1-14

T.O. 1F-4C-34-1-1

1-23). Safe escape considerations when firing the
20mm gun must include terrain avoidance, ricochet,
and secondary target explosions. The delivery con¬
siderations for firing upon a ground target are gen¬
erally the same as for bombing and rocket firing.

Wind correction and sight depression will be less
because of the projectile shorter time of flight. Like
the rocket launch tables, the sight setting is given as
a function of gross weight. Refer to the description
of the SUU-16/A gun pod and the 20mm ammunition.
When firing the guns in air-to-air gunnery, the lead
computing optical sight set (AN/ASG-22) functions to
position the sight reticle in azimuth and elevation and
satisfy the geometry of a lead pursuit course: (refer
to Air-to-Air Gunnery, this section).

LEVEL BOMBING

Level bombing (figure 1-14) is a special case of dive
bombing where the dive angle is zero; the delivery
parameters are basically the same. The approach
to the target is performed at a constant altitude,
wings level, and at a stabilized airspeed. After bomb
release, the aircraft may continue the approach
course and speed or perform the required escape
maneuver. Refer to Safe Escape, section V. The
weapons release computer set (WRCS) provides a
variety of delivery modes that can be used for level
bombing; dive toss (dive-level maneuver), dive lay-
down, laydown, or offset bombing. Refer to Weapon
Delivery Modes (F-4D), this section. The most sen¬
sitive parameters that affect bombing accuracy are
the release altitude above target and pitch attitude.
Refer to Altimeter Position Error Correction, sec¬
tion V. The method used to correct for wind effects
is determined by themethodof target tracking (crabbed
or drifting) and the type of weapon (high drag or low
drag). Refer to Wind Correction, section V.

RIPPLE RELEASE BOMBING

Ripple release bombing tables are provided in T.O.
1F-4C-34-1-2. Ripple release (figure 1-15) (dive or
level) delivery is identical to the single release with
the following additions:

a. Safe escape and dive recovery must be based on
the release altitude of the last bomb.

b. The sight setting or bomb range is computed to
place the center of the impact pattern on target.

c. . Wind correction is based on the time-of-fall of
the first bomb released.

d. The minimum release altitude for a level ripple
release is based on a straight ahead escape.

e. During the ripple release, a straight line flight
path must be maintained. The pipper will pass be¬
yond the target during the ripple release. (The first
bomb is released when the pipper is on target.)

When bombs are ripple released (BOMBS RIPPLE or
BOMBS TRIPLE) the release advance control can

be used with the WRCS delivery modes to place the
center bomb on target. The release parameters are
computed for a single bomb release.

LOW DRAG BOMB DELIVERY

Level bombing tables are provided in T.O. 1F-4C-
34-1-2. Lower release altitudes can be used (i.e.,

500 feet) if full military power is selected and a 4.0
G pullup is initiated immediately after bomb release
to attain a 20° to 30° climbing attitude. Refer to
Safe Escape, section V. Crosswind correction is not
required if the aircraft is crabbed to maintain a
ground track through the target. Rangewind correc¬
tion is not required if the bomb is released at a
ground speed that is equal to the preplanned true air¬
speed. Refer to Wind Correction, section V.

Dive bombing tables are provided in T.O. 1F-4C-34-
1-2 for all the low drag bombs and the practice
bombs. Refer to Safe Escape, the Fuze Arming
charts, and Dive Recovery chart to determine the
minimum release altitudes.

FIRE BOMB DELIVERY

Level bombing and dive bombing tables are provided
in T.O. 1F-4C-34-1-2 with dive angle from 0“ to 45 u .
The sight depression angle given in the tables is
computed to place the fire bomb on target; when it is
desirable for the fire bomb to hit short of the target,
the distance must be estimated or the sight setting
recomputed using the Sight Depression charts in sec¬
tion VI. Wind corrections can be applied in the same
manner as for the low drag bombs. Refer to Wind
Correction, section V. The Dive Recovery charts
must be used to determine the minimum release al¬
titude.

WARNING

DO NOT FLY through FIRE BOMB SMOKE
within 20 seconds of burst as a compressor
stall or flameout could occur.

CBU DELIVERY

The direct, dive laydown, laydown, or the offset
bombing delivery mode may be used to deliver the
CBU munition with either a single release or ripple
release. Low-level bombing, using the CBU munition
consists of a low-level or low-angle approach to tar¬
get at the predetermined speed and altitude above
target. Crosswind correction is applied (in addition
to crabbing the aircraft) by offsetting the flight path
parallel to, and upwind of the no-wind ground track.
Flight path offset, to correct for crosswind, is re¬
quired by the high-drag CBU munition because of
its longer time of flight. The optical sight establishes
the release point when the direct delivery mode is
used. The release point is automatically computed
and release is automatically initiated by the weapon
release computer set when the dive laydown, lay-
down, or offset bombing mode is used to deliver the
CBU munition. Rangewind correction may be ignored
for the CBU delivery. The bombing tables provide
the sight depression angle from flight path that will
place the first bomblet 500 feet short of the target.
When it is desirable to change the impact point of the
first bomb, the Sight Depression charts in section VI
must be used to establish the sight depression from
flight path.

1-38

T.O. 1F-4C-34-1-1

RIPPLE RELEASE )>-4D j

Range of First Bomb.

Range of Last Bomb.

Dive Angle.

Release Altitude of First Bomb.

Altitude Lost During Pullout.

Release Altitude of Last Bomb.

Number of Bombs Released.

Range from Release to center of pattern
Sight Depression.

Time of foil of first bomb.

Release Interval in Sec.

Pattern Length

DIVE DELIVERY

1 .

2 .

PRIOR TO TRP, SELECT LOFT DELIVERY MODE AND SET UP THE MULTIPLE WEAPON RELEASE MODE.

WHEN OVER TRP, THE AC DEPRESSES AND HOLDS THE BOMB RELEASE BUTTON TO START THE PULLUP TIMER, THE PULLUP LIGHT ILLU¬
MINATES AND THE HORIZONTAL AND VERTICAL POINTERS ON THE ADI CENTER.

WHEN THE STEADY TONE SOUNDS AND THE PULLUP LIGHT GOES OUT, ADVANCE THROTTLES TO FULL MIL POWER AND BEGIN PULLUP. (WITH
THE MOTOR DRIVEN TIMER INSTALLED, A 0.25-SECOND WARNING TONE IS GIVEN PRIOR TO THE STEADY PULLUP SIGNAL.) FLY TO KEEP THE
ADI POINTERS CENTERED UNTIL BUFFET ONSET, THEN FOLLOW THE BUFFET BOUNDARY.

WHEN THE SELECTED RELEASE ANGLE IS ACHIEVED, THE PULLUP LIGHT ILLUMINATES, AND THE STEADY TONE STOPS THE AC WILL
CONTINUE TO HOLD THE BOMB RELEASE BUTTON DEPRESSED UNTIL THE LAST BOMB IS RELEASED.

WHEN THE LAST BOMB IS RELEASED, INITIATE A WINGOVER TO ACHIEVE A 120° TURN WHILE DIVING TO ESCAPE AT MINIMUM ALTITUDE.

F4D-34-I-203

Figure 1-15

1-39

T.O. 1F-4C-34-1-1

When the dive delivery is used, a straight
line flight path should be maintained during
the release and for 2 seconds alter the re¬
lease; the minimum release altitude should
be planned accordingly.

CBU DELIVERY USING THE SUU-7 DISPENSER

When a dive delivery is used for CBU series weapons
using the SUU-7 dispenser, a straight line flight path
should be maintained during the release and for 2
seconds after release. The minimum release altitude
should be based on altitude lost during recovery plus
altitude lost during the 2-second stabilized dive
after release. This procedure is necessary to pre¬
vent voids in the bomb impact pattern whether using
dispensers with or without modified tube extensions.
The above procedure must be used when the dispenser
is not modified with tube extensions to prevent bomb
hang-up and possible subsequent early detonations.

Do not release bombs from unmodified SUU-7
dispensers (without tube extensions) while the
aircraft is in other than wings level stabi¬
lized flight.

HIGH DRAG GP BOMB DELIVERY

The high drag GP bombs can be delivered from alti¬
tudes between 100 feet to 3000 feet depending upon the
bomb used, the fuzing limitation, fragmentation en¬
velope and dive angle. The high drag characteristic
provided by the retarder tail fin assembly reduces
the bomb range and increases the bomb time of fall
and impact angle. Single release bombing tables and
ripple release bombing tables are provided in T.O.
1F-4C-34-1-2. Use the fuze Arming and Safe Escape
chart, section VL

DO NOT FLY over or near burst area within
20 seconds of detonation as aircraft damage
can result from flying debris. During train¬
ing missions, at least 20-seconds spacing be¬
tween aircraft must be observed when inert
or sand filled bombs are released. In the
training situation, observing the 20-second
spacing between aircraft prevents a bomb-
to-aircraft collision in the event a bomb re¬
leases low drag and ricochets into the air
after impact.

MK82 (SNAKEYE I) AND M117R HIGH/LOW DRAG
OPTION, IN-FLIGHT SELECTIVITY

The MK 82 (Snakeye I) and M117R GP bombs can be
released in a low drag configuration (retarding fins
remain closed) or a high drag configuration (retarding
fins open after release) provided arming wire routing
is accomplished during loading to provide these op¬
tions. The high or low drag configuration is selected
in flight through the arm nose tail switch on the mul¬
tiple weapons control panel. Refer to Arming Wire/
Lanyard Routing, part 4, for detailed information
concerning the required arming wire configuration
for this capability.

For a high drag release using the in-flight option, the
NOSE & TAIL position is selected on the arm nose
tail switch. The NOSE position is selected for a
low drag release with only the nose fuze initiated.
After T.O. 1F-4-805, the TAIL position may be se¬
lected for a high drag release with only the tail fuze
initiated.

Since certain mechanical and human errors
inherent with this type delivery option can
result in hazardous or degraded reliability
situations, the operational commander should
consider the following notes and warning
which point out the possibility of self inflicted
damage, injury to friendly ground forces,
single fuze reliability, and delivery accuracy
degradation before approving this option for
operational use.

Note

With the approved arming wire routing for
the in-flight high/low drag option, single
fuze reliability (nose fuze only) is available
with the low drag option. Dual fuzing reli¬
ability (nose and tail) is available with the
retarded high drag option if the high drag
bomb time of fall exceeds 6.6 seconds. If
the high drag bomb time of fall is less than
6.6 seconds, only FMU-54 tail fuze arming
is available. Single fuze reliability (tail fuze
only) is available with the high drag option
when the arm nose tail switch is positioned
to TAIL.

• When the MK 82 Snakeye I or M117R bombs
are configured for inflight selectivity for
high/low drag releases, the minimum nose
fuze setting is 6.0 seconds for the M904E2
or M904E3 fuze; the minimum tail fuze set¬
ting for the FMU-54 fuze is 2.5 seconds.
With current arming time tolerances, the
minimum bomb time of fall to provide time
for the fuzes to arm is 6.6 seconds for the
nose fuzes and 2.8 seconds for the tail fuze
(high drag arming only).

1-40

Change 4

T.O. 1F-4C-34-1-1

WARNING

• Under combat conditions, where a 6 second
nose fuze arming delay setting may be incon¬
sistent with operational requirements, a 4
second M904E2/E3 nose fuze arming delay
setting may be used subject to the following
restrictions:

• Dive Releases. For planned high drag dive
releases, the release altitude must not
exceed 1000 ft AGL.

• WRCS Dive-Toss Releases. For planned high
drag dive toss releases, the pickle altitude
must not exceed 1000 ft AGL.

• Level Releases. For planned level releases
of high drag weapons and a straight and level
escape maneuver, the release altitude must
not exceed 250 ft AGL. This restriction does
not apply for a single, pairs, or salvo type
release if a 4G wings level pullup or a 4G
60° banked turn escape maneuver is executed
immediately after release.

Note

None of the foregoing restrictions apply if
the planned high drag bomb release altitudes
exceed the minimum release altitudes that
are required for safe escape for low drag
MK 82 bombs.

WARNING

* With this in-flight option of high/low drag
selection, strict adherence to the prescribed
cockpit switchology is mandatory. If the AC
inadvertently selects high drag, or experi¬
ences an arming solenoid malfunction when
the intent is to release a low drag bomb, a
fully armed high drag bomb would impact
considerably short of the intended aimpoint.

If friendlies are in the immediate area, this
could result in disastrous consequences.
Conversely, if the AC inadvertently selects
low drag, or experiences an arming solenoid
malfunction when the intent is to release a
high drag bomb during close-in attack condi¬
tions, the result (if the bomb time of fall is
less than 6.6 seconds) would be an unarmed
bomb with an initial impact considerably
downrange of the intended impact point. This
could also result in disastrous consequences
if friendlies are in the area; particularly if
the bomb detonates, or ricochetes and then
detonates. If the bomb time of fall exceeds
6.6 seconds in this case, a fully armed low
drag bomb would impact considerably down-
range from the intended impact point.

* There is also a possibility of the delivery
aircraft suffering self-inflicted fragment
damage if an intended high drag bomb releases
low drag during a close-in attack condition,
and for some reason detonated at initial im¬
pact. To provide an additional margin of
safety in this event, the pilot should execute
a 4-G pullup or a 4-G, 60° banked escape
maneuver immediately after release.

• Minimum release altitudes with respect to
fragment envelope clearance should be ob¬
served even if the bomb is released SAFE.
This would protect the aircrew in the event
of an arming wire hang-up, solenoid mal¬
function, etc, resulting in an arming wire
being extracted and the bomb becoming fully
armed.

Note

WARNING

LEAFLET BOMB DELIVERY

The weapon release computer set can be used to lo¬
cate the target and automatically release the leaflet
bomb. The offset bombing mode, the laydown mode,
the dive laydown, or the direct delivery mode can be
used for leaflet bombing. The M129E1, E2 leaflet
bomb is released from altitudes of 4000 feet through
11,000feet. The bombing table T.O. 1F-4C-34-1-2
states the bomb time of flight and range from release to
burst for a given level flight release true airspeed
and release altitude above target. The time of flight
is used to set the mechanical time delay fuze for a
3000-foot detonation. The bomb range is used to es¬
timate the release point. Various wind effects on the
bomb prior to burst is a function of wind velocity and
bomb time of flight. The wind effect on the leaflets
after detonation and during the descent is difficult, if
not impossible, to predict.

FLARE DISPENSING

The SUU-25A/A, B/A, C/A flare dispenser is used to
deliver the MK 24 flares. The delivery aircraft ap¬
proaches the target in level flight at the preplanned

Change 9

1-40A

T.O. 1F-4C-34-1-1

release altitude. The MK 24 flare profile and param¬
eters are illustrated in figure 1-16. Release airspeed
is not a critical parameter. Release altitude is crit¬
ical only when it is desirable to have flare burnout
above the ground. The flare dispensing table T.O.
1F-4C-34-1-2 provides the minimum release altitude
AGL for flare burnout at impact. The desired burn¬
out altitude AGL must be added to the minimum re¬
lease altitude AGL to determine the actual release
altitude AGL. The flare dispensing table also pro¬
vides the horizontal distance traveled and vertical
drop of the flare prior to ignition. The flare ejection
fuze delay time and the flare ignition fuze delay time
is set according to mission requirements and the data
on the flare dispensing table. To properly position
the flare at ignition, rangewind effect and crosswind
offset (ft) may be determined by multiplying the
rangewind or crosswind component (kts) times 1.7
times the sum of the ejection and ignition fuze delay
settings.

LOFT BOMBING

Note

On F-4D-32 and up; and all others after T.O.
1F-4-702, the aircrew may energize and use
the WRCS target find mode along with any
LABS mode selected, including DIRECT. The
modification includes the addition of the weap¬
on delivery panel (figure 1-17) added to the
rear cockpit. Refer to LABS/WRCS Delivery
Mode, this section.

The loft bombing mode combines the use of the multi¬
ple weapons release system (MWRS) with the attitude
reference and bombing computer set (ARBCS). The
purpose of the loft bombing mode is to provide rip¬
ple relase capability of GP bombs from low altitude
with a minimum of aircraft exposure time to ground-
fire and without a target fly-over. This is accom¬
plished as illustrated in figure 1-15.

1-40B

Change 9

T.O. 1F-4C-34-1-1

WK 24 FLARE PROFILE |3fljI

Release

D Minimum release altitude AGL required to
provide|flare burnout.

0 Vertical drop prior to flare ignition.

B Ejection fuze delay time.

□ Ignition fuze delay time.

0 Flare Burning Time:

a. Mod 3: 180 sec.

b. Mod 4: 198 sec.

B Desired flare burnout height AGL.

H Horizontal flare travel prior to ignition.

-- 4C-34- 1 - 1 -(19)

Figure 1-16

During mission planning, an IP (Identification Point)
is selected on the target map, or photos, that is lo¬
cated near and on course to the target; the pullup
point is established: the release angle of the first and
last bomb, the pattern length of the bombs, and the
pullup timer setting are also defined.

Prior to the bombing run, the pedestal panel is set
up for a bombs ripple release with the master arm
switch in ARM and the stations selected; and the de¬
livery mode selector knob is positioned to LOFT.

The LABS bomb release angle computer automati¬
cally initiates the ripple release when the aircraft
pitch attitude is equal to the preset release angle.
The approach to the IP is performed at a preplanned
altitude AGL and airspeed. At the IP, the bomb
button (pickle button) is depressed and must be held

energized until the final bomb is released. Depress¬
ing the bomb button starts the pullup timer. At the
completion of the pullup timer, a pullup signal is
given and the AC begins a 4 G in 2 seconds pullup.
When the aircraft attitude is at the preselected angle
the bomb release angle computer automatically ini¬
tiates the ripple release. The AC continues the
pullup until the last bomb is released. When the last
bomb is rippled off, the bomb button is released, and
the AC begins a wing-over escape maneuver to
achieve a 120° turn while diving to escape at mini¬
mum altitude.

Note

After T.O. 1F-4-702, the gyro FAST ERECT
switch is added to the aux. armament control
panel (figure 1-17). The AC may use the
switch to momentarily cage the AN/AJB-7
gyros and correct any gyro precession
during the level, constant speed target run-in.

Refer to LABS/WRCS Delivery Mode, this
section.

The following is a more descriptive analysis of the
LOFT release system function. When LOFT is se¬
lected and the optical sight is operated in the A/G
mode, the optical sight is pitch stabilized with ref¬
erence to the horizontal platform, and can be manu¬
ally depressed. The sight is not drift stabilized. The
sight reticle light will follow the pullup indications
(pullup light ON - reticle light ON, pullup light OFF -
reticle light OFF). Either bomb button (front or rear
cockpit) is depressed over the IP. This starts the
pullup timer countdown. Refer to Loft Bombing Con¬
trols, this section. Bomb button power also ener¬
gizes relays which illuminate the pullup light, and
which move the horizontal and vertical pointers of
the ADI into view over the center of the sphere. The
vertical pointer indicates yaw/roll light deviations
and the horizontal pointers show deviations from
1.0 G flight. The appearance of the pointers indi¬
cates that the ARBCS lias properly switched into the
LOFT bombing function. At the end of the total time
interval, pullup voltage is applied to the tone genera¬
tor producing a continuous audible tone. The pullup
light circuit is deenergized and the light goes off.
These are the direct indications to begin pullup. The
AC should select MIL power and begin rotation into
the pullup maneuver. As the timer-complete contacts
close, voltage is applied to one side of the low and
high angle release switches, which are not yet ener¬
gized. Relays in the flight director bombing com¬
puter are energized to start the G programmer. The
ADI horizontal pointer now indicates G error based
on 4 G obtained in 2 seconds. The horizontal pointer
deflects upward unless the AC begins pullup.

When the aircraft reaches the preset pitch attitude,
the release angle switch closes and applies the re¬
lease signal. As release voltage is applied, the tone
generator is deenergized, the timer is reset, and
the pullup light illuminates. This is the signal that
automatically begins the ripple release. The AC con¬
tinues to hold the bomb button depressed and the G
program will continue to be displayed by the ADI
horizontal pointer as an aid in completing the maneu¬
ver. The vertical pointer, however, is deflected out

Change 5

1-41

T.O. 1F-4C-34-1-1

of view at release. When the AC releases the bomb
button, all bombing voltage is removed and the hori¬
zontal pointer deflects out of view, and the pullup
light goes off.

Note

During the LOFT mode, once the bomb button
is depressed, it must remain depressed until
final bomb release. If the bomb button is re¬
leased before the first bomb is released, an
interlock circuit is energized and the run can¬
not be continued by depressing the bomb but¬
ton. To overcome the interlock, the bomb
mode selector knob must be positioned out of
the LOFT function and then returned to LOFT.

The LADD bombing system can be used to perform
the loft bomb delivery. This is accomplished by se¬
lecting the LADD mode on the bomb mode selector
switch and setting the pullup to release time (from
the bombing tables) on the Release Timer. The re¬
lease signals are the same as for the loft bombing
mode. The horizontal needle on the ADI sphere will
program 3.5 G in 1.5 seconds (not 4.0 G in 2 seconds
as for the loft mode) until approximately 38° pitch
attitude is achieved. Therefore, the ADI cannot be
used above 38° when the LADD bombing system is
used to accomplish the loft delivery, the aircraft
accelerometer must be used to establish the pullup
acceleration until buffet onset.

AIRCRAFT WEAPON SYSTEM CONTROLS (F-4D)

The following is a general description of the controls
and indicators (figure 1-17) that comprise the F-4D
non-nuclear weapon delivery system. The controls
and indicators are described briefly to augment the
detailed description of various delivery modes which
follows. The following major components comprise
the non-nuclear weapons delivery system, excluding
air-to-air missile delivery.

a. Delivery mode selector panel.

b. Weapon delivery panel.

c. Station and weapon selection panel.

d. Weapons release computer set (WRCS) AN/
ASQ-91.

e. Lead computing optical sight system (LCOSS)
AN/ASG-22.

f. Inertial navigation set (INS) AN/ASN-63.

g. AN/APQ-109A radar set.

h. Attitude reference and bombing computer set
(ARBCS) AN/AJB-7.

DELIVERY MODE SELECTOR PANEL

The delivery mode selector panel (figure 1-17) is in
the front cockpit on the main instrument panel, plac¬
arded LABS on the left, and WPN REL on the right.
The selector knob is used to select one of twelve
delivery modes. The six LABS delivery modes are
placarded DIRECT, TIMED LEVEL, TIMED LADD,
TIMED O/S, LOFT,and INST O/S. The DIRECT
position is used for bombing, rocket, or gun firing
with a fixed, depressible sight. The LOFT position
is used to perform the loft bomb ripple release mode
(see the preceding note). The OFF position removes
power from the WRCS on the LABS bombing modes
thereby preventing a release signal from reaching
the bomb release relay. The guns and AIM missiles
can be fired with the mode selector switch in the
OFF position or any other position. The six WRCS
delivery modes are on the right side of the mode

selector knob, placarded WPN REL: TGT FIND
(target finding), DIVE TOSS, DIVE LAY (dive lay-
down), LAYDOWN, OFFSET BOMB, andAGM-45.
The nuclear stores jettison button is in the center of
the mode selector knob, placarded NUCLEAR PUSH
TO JETT; refer to Jettison Controls, this section.

WEAPON DELIVERY PANEL

The weapon delivery panel contains the switches by
which the aircrew may select an integrated AJB-7/
WRCS delivery mode. The three switches on this
panel are described with the delivery mode. For a
description of the system, refer to LABS/WRCS
Delivery Mode.

STATION AND WEAPON SELECT
PANEL

The station and weapon select panel (figure 1-17), on
the front cockpit pedestal, contains the switches that
control and select all phases of non-nuclear weapon
delivery, excluding air-to-air missile delivery.

MASTER ARM SWITCH

The master arm switch has two positions, SAFE and
ARM. hi ARM, power is supplied to the bomb button
transfer relay and the arm nose tail switch. Applica¬
tion of power energizes the bomb button transfer
relay and the function of the bomb button (pickle but¬
ton) is transferred from the nuclear weapons system
to the non-nuclear weapons system. (Refer to Bomb
Transfer Relay, this section.) The switch must be
in ARM to deliver all non-nuclear weapons, excluding
air-to-air missiles. Nuclear weapons can be

1-42

Chang* 2

T.O. 1F-4C-34-1-1

CONTROLS AND INDICATORS

FRONT COCKPIT

STATION WEAPON SELECT

HHHBB?:

GUNS 4 AUTO
stores CltAt

NQB MAI SCNlltAt

no i com

A* AND2

BEADY

BUD FED
ADJUST

GUNS &
STORES

AUTO

CltA*

SAND I

I NORM

|NORM

FWO/

JEST

RETICLE

DEPRESSION

KNOB

INDEXER LIGHTS

(AGM-45 ONLY)

NUCLEAR

JETTISON

BUTTON

OPTICAL SIGHT

DELIVERY
MODE SELECTOR
KNOB

STATION

SELECT

BUTTONS

MASTER

ARM

SWITCH

GUNS
& STORES
SWITCH

CONTROL

ARM NOSE/
TAIL SWITCH

PEDESTAL PANEL

MISSILE STATUS
PANEL

F-4D-30 THRU 33 BEFORE
T.O. 1F-4D-559.

AFTER T.O. 1F-4D-559

Di FILTER SWITCH

Figure 1-17 (Sheet 1 of 3)

MlSSili n STATUS

* y

o I

t FWO OFF f/«»

LREADY

; 1 \ I '

o V v — c

(st t H*n

l AM R AFT

' V’

WEAPON

SELECT

KNOB

CL TANK
ABOARD

LIGHT

■

SHUTTER I
LEVER |

RETICLE

INTENSITY

KNOB

T.O. 1F-4C-34-1-1

C0NH01S AND INDICATORS jgfil

FRONT COCKPIT

DCU-94 A CONTROL MONITOR
F-4D thru Block 33

1^ Block 32 and Up.

Block 24 thru 31, After T.O. 1F-4-702.

E> Block 32 thru Block 33.

Block 24 thru Block 31 Alter
incorporation of T.O. 1F-4D-513.

F4D-34-I-205-2

Figure 1-17 (Sheet 2 of 3)

1-44

Change 3

1-45

T.O. 1F-4C-34-1-1

released and air-to-air missiles can be launched re¬
gardless of the master arm switch position. Air-to-
air missiles can not be launched if the trigger trans¬
fer relay is energized. The trigger transfer relay
can not be energized until the bomb button transfer
relay is energized. Refer to Trigger Transfer
Relay.

STATION SELECTOR BUTTONS

The five station selector buttons are push-on push-
off switches, placarded LO (left outboard), LI (left
inboard), CTR (center), RI (right inboard) and RO
(right outboard). The buttons remain in detent when
pushed off. The top half of the button illuminates
green when the button is pushed ON and goes out when
pushed OFF, regardless of the position of the master
arm switch. With the master arm switch in ARM,
the bottom half of the station selector button illumi¬
nates amber to indicate that a weapon is aboard if
the MER/TER stepper switch is positioned on an
active position (1 thru 6 or 1 thru 3). The amber
light will not illuminate if the MER/TER is not
homed or is OFF. Therefore, a hung bomb would
not produce an amber light until the MER/TER is
rehomed by selecting RKTS & DISP. The amber
light may blink (depending on the stations loaded)
while the stepper switch is recycling to the first
loaded station encountered, and illuminate steady
when positioned on a loaded station. The light illu¬
minates when RKTS & DISP is selected even when
bombs are aboard. The amber light illuminates
when a single weapon is loaded directly to the MAU-12
armament pylon and goes off when the weapon is
released or jettisoned. The amber light goes out
when all weapons from the station are released, or
CBU's fired. When CBU dispensers are aboard,
the light begins flashing when any of the CBU dis¬
pensers on the selected station has two releases
remaining, and goes out when all CBU dispensers
on that station are empty. The amber light will not
go out when all rocket pods or flare dispensers from
the station have been fired out. When the AC selects
BOMBS to release the empty CBU dispensers, the
amber light illuminates, then goes out when the AC
releases the empty rocket pods or empty CBU dis¬
pensers. The CBU indicating function of the amber
light is present only when the weapon selector knob
is in RKTS & DISP, and all MER and TER stow plugs
are installed. The lights are connected to the warn¬
ing light dim and test circuitry.

The empty CBU indication establishes that all
explosive detents in the dispenser (s) have been
fired. The possibility of a hung bomblet(s)
remaining in the tube(s) can not be assessed
by the aircrew.

The station select buttons (outboard) imme¬
diately energize the SUU-23 gun pod prestart
circuits and start the gun inertial motor. To

avoid inertial motor burn-out,avoid selecting
the stations during ground operations or any
operations not directly involving the gun pod.

WEAPON SELECTOR KNOB

The weapon selector knob is a rotary type switch with
eight positions, used to select the type of weapon
(bomb, rockets, guns, or AGM missiles) and the re¬
lease or firing sequence (single, triple, or ripple).
Refer to figure 1-18, F-4D Normal Release Sequence.
When the BOMBS positions are selected, the selec¬
tion on the delivery mode selector panel may be in
any bombing mode to obtain a bomb release. When
the RKTS & DISP position is selected to fire the
rocket launchers, only the DIRECT position on the
delivery mode selector panel can be used. When the
RKTS & DISP position is selected to fire the CBU or
flare dispensers, the selection on the delivery mode
selector panel may be DIVE LAY, LAYDOWN, OFF¬
SET BOMB, or DIRECT.

Note

When the weapon select knob is in the AGM-45
position, ER missile status and the audio tone
is not available until the missile arm switch
is in ARM.

Bombs/Single

When the weapon selector knob is positioned to
BOMBS/SINGLE, one bomb is released from each
station selected when the bomb release button is
depressed. If five stations are selected and loaded,
five bombs are released simultaneously .

Bombs/Triple

When the BOMBS /TRIPLE position is selected and
the bomb release button held depressed, three bombs
are ripple released, regardless of the number of
stations selected, in a timed interval established by
the position of the interval switch: 0.06 SEC, 0.10
SEC. or 0.14 SEC. The bomb release button must be
held depressed until the three bombs are released.
When a left and a right station is selected, the re¬
lease pulse is directed alternately between the left
and right station to releas e two bombs from one
side and one bomb from the other side. There is no
provision for determining which side receives the
first release signal, the left station or the right sta¬
tion.

Bombs/Ripple

When BOMBS/RIPPLE is selected and the bomb re¬
lease button is held depressed, the selected bombs
are released singularly in a timed interval estab¬
lished by the position of the interval switch. Bombs
continue to be released until the bomb button is re¬
leased. The bombs are released alternately from
the left and right wing stations. When five stations
are selected, all the bombs from the outboard sta¬
tions are released, then the inboard station, and
finally the centerline station. (If the pilot selects
both stations on one wing, i.e., LO and LI, then

1-46

T.O. 1F-4C-34-1-1

NORMAL RELEASE SEQUENCE F-4DI

5 STATIONS LOADED, 5 STATIONS SELECTED

SINGLE

Each bomb button signal simultaneously
releases one bomb from each selected
station.

RIPPLE

Holding the bomb button depressed releases
bombs continuously in the left-right order
and at the selected bomb release interval.

Note

When two or more stations are selected,
there is no indication which station
receives the first release pulse, left or
right. Normally, the left station
receives the first release pulse.

TRIPLE

•O#

1 RELEASE PULSE

Holding the bomb button depressed releases
three bombs in the ripple release sequence
and at the selected bomb release interval.

mom

The MER and TER release
sequence always remains as
illustrated here. Empty
points are automatically
stepped over.

TER
SEQUENCE

MER
SEQUENCE

ooo

—— u *

24 RELEASE PULSES

3 RELEASE PULSES

€>

F4D-34I-206

Figure 1-18

1-47

T.O. 1F-4C-34-1-1

weapons release alternately from each of the sta¬
tions.) There is no provision for determining which
side (left or right wing station) receives the first
release pulse; normally the left side receives the
first release pulse.

Rockets and Dispenser/Singie

Note

When the SUU-21/A dispenser is loaded on
the inboard station, bomb release will not
occur if the weapon selector knob is on
RKTS & DISP.

Selecting RKTS & DISP and depressing the bomb re¬
lease button will fire-out one rocket pod or release
a predetermined number of tubes from one dispenser,
from each station selected. If five stations are se¬
lected, five rocket launchers will fire-out simultane¬
ously. Only the DIRECT position can be used to fire
the rocket launchers.

Rockets and Dispenser/Ripple

Note

The firing pulse in the ripple mode is not suf¬
ficient duration to completely fire-out the
entire rocket launcher.

With RKTS & DISP/RIPPLE selected and the bomb
release button is held depressed, the selected dis¬
pensers will be fired singly in a timed interval estab¬
lished by the position of the interval switch, 0.06
SEC, 0.10 SEC, or 0.14 SEC. Ripple firing pulses
continue until the bomb button is released. The fir¬
ing pulses alternate between the left and right station.
When five stations are selected, only the outboard
station CBU is fired out. The firing pulses will not
transfer to the inboard stations until the outboard
station selector buttons are pushed OFF. Likewise,
the firing pulses will not transfer from the inboard
stations to the centerline station until the inboard
station selector buttons are pushed OFF. There is
no provision for determining which station (left or
right) receives the first firing pulse.

Guns

The gun pods are selected by placing the weapon se¬
lector knob to GUNS, depressing the LO, CTR or RO
station selector buttons, and placing the master arm
switch to ARM. The gun located on the station(s) se¬
lected will receive firing voltage when the trigger
switch is pulled. The guns can also be selected and
fired, regardless of the weapon selector switch posi¬
tion, when the guns and stores switch is positioned to
GUNS & STORE, the master arm switch is in ARM,
and the gun station selected. The centerline gun can¬
not be fired if the nose gear is extended; this will not
affect the firing capability of the outboard guns. Re¬
fer to Trigger Switch and Trigger Transfer Relay.

A/G Missiles

The A/G MISSILES position is not a safe position for
bombs. Bombs are released when the station is se-

1-48 Change 6

lected and the bomb button depressed, as if BOMBS
SINGLE is selected. The A/G missile position is
used to select the AGM-12B/C missile and the AGM-
45 missile. The AGM-45 placard is changed to AGM-
45/62 to include the selection of the MK 1 MOD 0
guided weapon.

Arm Nose Tail Switch

This switch (figure 1-17) completes the circuit be¬
tween the master arm switch and the arming solenoids
in the aircraft ejector racks (MAU-12, BRU-5/A,
and MER/TER). The energized solenoids retain the
arming wire swivel loops and as munitions are ejected,
the arming wires are pulled to initiate the fuze arm¬
ing sequence. In the SAFE position, the armingwires
are retained by the munition during separation from
the aircraft and the associated fuze remains SAFE.

The arm nose tail switch also provides the selective
high/low drag capability for those weapons which
may be rigged for either a freefall or retarded drop.
In this case, the solenoids are energized to apply the
holding force for the lanyards which deploy the re¬
tardation device. (Refer to M117R and MK 82 Snakeye
I bombs, and Arming Wire Routing, part 4.)

WARNING

The switch positions and corresponding solenoids
armed are shown below.

Switch Position

SAFE

NOSE

TAIL

NOSE & TAIL

Solenoid Armed
None

Fwd and Ctr
Aft

Fwd, Ctr, and Aft

There is no center solenoid on the MER/TER and
BRU-5/A ejector racks.

With MER/TER equipment that do not have automatic
homing, the arm nose tail switch must be in the
NOSE or NOSE & TAIL position to apply power through
the sensing switch to the MER/TER stepper solenoid.
Then with a partial load of bombs aboard, the empty
stations are bypassed and the AC releases one bomb
with each pickle signal. The TAIL position does not
apply the stepping voltage and an extra pickle must
be delivered to step through each empty MER/TER
station.

With MER-10A and TER-9A equipment that have auto¬
matic homing, empty stations are bypassed regard¬
less of the arm nose tail switch position.

T.O. 1F-4C-34-1-1

INTERVAL SWITCH

The interval switch is used only during BOMBS/
RIPPLE, BOMBS/TRIPLE, and RKTS & DISP/RIP-
PLE modes on the weapon selector knob, to establish
interval between each release. The switch has three
positions (0.06 SEC, 0.10 SEC, and 0.14 SEC) that
determine the pulse interval: the pulse length or
duration is always the same (23 to 33 milliseconds).
The pulse rate is measured from the start of each
pulse and therefore includes the pulse duration. The
pulse rate tolerance of the various release intervals
are: 60 to 90, 100 to 115, and 140 to 161 millisec¬
onds.

GUNS AND STORE SWITCH

The guns and store switch has two positions placarded
GUNS & STORE and NORMAL. The purpose of the
guns and store switch is to permit the AC to fire the
guns regardless of the weapons selector knob posi¬
tion. Placing the switch to GUNS & STORES performs
the same function as placing the weapons selector
knob to GUNS; however, the function of the optical
sight is determined by the delivery mode and weapon
selected. When the switch is positioned to NORMAL,
the guns cannot be fired unless the weapon selector
knob is in GUNS.

GUN CLEAR SWITCH

The gun clear switch has two positions (AUTOCLEAR
and NONCLEAR) to select the gun mode of operation.
When the autoclear mode is used, unfired rounds
are extracted from the gun and ejected overboard.
When the nonclear mode is used, the unfired rounds
remain the gun. The NONCLEAR position is se¬
lected when the gun is to be fired in short bursts.
When the guns have been fired in the NONCLEAR
mode and not completely fired out, a final burst must
be fired with the switch positioned to AUTO-CLEAR
to clear the guns. If the gun is fired out in the NON¬
CLEAR mode, the bolt assemblies automatically
clear.

REJECT SWITCH

The reject switch is applicable to the AGM-45 mis¬
sile DF control circuits. Refer to the AGM-45 mis¬
sile system in T.O. 1F-4C-34-1-1A.

BAND SWITCH

The band switch is intended for use with the AGM-45
missile system. The switch, however, has no func¬
tion at the present time.

Change 4

1-49

T.O. 1F-4C-34-1-1

FILTER SWITCH

The filter switch is functional in the filter control
network of the Mark 1 Mod 0 weapon. See T.O. 1F-
4C-34-1-1A.

Note

If the aircraft is configured withaSUU-42A/A
jumper bundle (53-09790-107) at the outboard
stations, the filter switch must be maintained
in the RED position to get release and trans¬
fer voltage to the inboard and CL stations.

TRIGGER SWITCH

The front cockpit trigger switch is on the control
stick. When the spring-loaded switch is actuated,
power is supplied to the clutch/brake solenoid to ini¬
tiate gun rotation and start the ammunition feed sys¬
tem. The gun will start firing when the trigger switch
is pulled and cease firing when the trigger is released.
Power can be removed from the trigger switch by
pulling the gun power circuit breaker. No. 1 panel.
The trigger switch in the aft cockpit is always in¬
operative. Refer to SUU-16/A-23/A Gun Pod, this
section. For missile launching, refer to T.O. 1F-
4C-34-1-1A.

WARNING

The trigger switch requires very little move¬
ment to initiate gun firing; therefore, the AC
should place his finger on the trigger only
when the gun is to be fired.

Trigger Transfer Relay

The trigger transfer relay must be energized to fire
guns and must be deenergized to launch air-to-air
missiles. To fire guns, the trigger transfer relay is

energized by selecting guns and energizing the bomb
button transfer relay as follows:

a. The bomb button transfer relay can be energized
by positioning the master arm switch to ARM, and
the DCU-94/A master release lock switch AFT.

b. Guns can be selected by positioning the weapon
selector knob to GUNS or by positioning the guns and
stores switch to GUNS & STORES.

Note

• When the trigger transfer relay is energized,
all missile status lights on the missile status
panel will go out. The TK light remains on if
the tank aboard relay is energized. The
tuned-up status of the missiles is not affected.

• The nose gear up limit switch must be ener¬
gized to fire the centerline gun pod. The out¬
board gun pods can be fired regardless of the
nose gear up limit switch position.

To launch air-to-air missiles, the trigger transfer
relay must be deenergized. If guns are selected,
the trigger transfer relay is deenergized by posi¬
tioning the master arm switch to SAFE.

AIR REFUELING RELEASE (ARR) BUTTON

AIM-4D Coolant Supply Mode

(AFTER T.O. 1F-4D-508).

Refer to T.O. 1F-4C-34-1-1A section I, part 4, AIM-
40 Missile and AIM-9 Missile.

RETICLE CAGING MODE

(AFTER T.O. 1F-4D-514).

Refer to Lead Computing Optical Sight, this part.

1-50

Change 6

T.O. 1F-4C-34-1-1

BOMB BUTTON

The bomb or pickle button (figure 1-17) is a small red
button on the left side of the control stick grip in the
forward and rear cockpit. The button is spring-
loaded to OFF. Depressing the bomb button (in either
cockpit) releases all air-to-ground weapons selected
on the multiple weapons control panel or the DCU-
94/A monitor-control panel. Power can be removed
from the bomb button by pulling the A/G weapon re¬
lease cont circuit breaker, No. 1 panel.

Bomb Button Transfer Relay

The bomb button transfer relay transfers the release
signal, when energized, from the DCU-94/A panel
controls to the pedestal panel controls. The relay is
energized when the master arm switch is positioned
to ARM, providing one of the following switches is
positioned AFT or SAFE:

a. DCU-94/A all station selector switches - AFT.

b. DCU-94/A master release lock switch - AFT.

c. Nuclear store consent switch - SAFE.

If one of the station selector switches, the master
release lock switch, and the nuclear store consent
switch are energized, the bomb button transfer relay
deenergizes (nuclear release) regardless of the mas¬
ter arm switch position.

Note

The DCU-94/A UNLOCKED lights for the
wing stations (except the RO) illuminates
when power is applied to the aircraft, if the
inflight lockout pins are installed in the
armament pylons.

AUTOMATIC ACQUISITION SWITCH

(After T.O. 1F-4D-513)

The automatic acquisition switch is on the left throttle
handle (figure 1-19). The landing lights switch,
formerly on the left throttle handle, is now on the
left vertical panel in the vacancy provided by elimi¬
nation of the emergency speed brake retract switch.

The purpose of the automatic acquisition mode is to
provide the AC with the capability to lockon a target
with the aid of the optical sight. With the sight in
(A/A) air-to-air the sight line will be parallel with
the radar boresight line. Refer to T.O. 1F-4C-34-1-

Figure 1-19

1A for a complete description of the operational ap¬
plication.

PULLUP LIGHT

The pullup light on the front cockpit instrument panel
is a press-to-test type light. The lamp intensity can
be controlled by rotating the outer ring to vary the
size of the iris over the lamp. The pullup light illu¬
minates when a bomb release signal is generated and
goes out when the bomb button is released. For the
description of the pullup light function during the loft
bombing mode, refer to Loft Bombing, this section.

PULLUP TONE

(After T.O. 1F-4D-516)

An audio tone is present in the headset (for all WRCS
modes except AGM-45) when the bomb button is de¬
pressed and continues until a bomb release signal is
generated. The tone is generated by the AN/AJB-7
audio tone generator and is not broadcast. For a
description of the audio tone function during the loft
bombing mode, refer to Loft Bombing, this section.

Change 2

1-51

T.O. 1F-4C-34-1-1

^—(23)

BALLISTIC COMPUTER ADJUSTMENTS / F-4D

Note

REFERT
DRAG CO
COMPUTE

D SECTIO
EFFICIEN
R SETTIf*

N VI WRCS
TS FOR

ACCESS DOOR 19

Figure 1-20

PULLUP TONE CUT OFF SWITCH

The pullup tone cut-off switch is on the left console,
rear cockpit. The switch enables the aircrew to pre¬
clude external transmission of the audio tone during
any bombing mode in which the tone signal is in¬
volved. With the switch in TONE ON, the audio tone
signal is transmitted through the UHF transmitter.
The TONE OFF position deenergizes the same tone
transmit circuit. In either case, the aircrew hears
the tone and all tone functions remain the same.

WEAPONS RELEASE COMPUTER SET

The AN/ASQ-91 weapons release computer set
(WRCS) is designed to aid the aircrew in the delivery
of non-nuclear weapons. The WRCS has two low-
level bombing modes, LAYDOWN and DIVE LAY-
DOWN and two navigational modes, TARGET FIND¬
ING and OFFSET BOMBING that aid the aircrew in
locating the target and performing a low-level bomb¬
ing mission.

The WRCS consists of three units (figure 1-21): the
ballistics computer in door 19; the weapons release
computer control panel (WRCS panel); and the cursor
control panel, in the rear cockpit on the right con¬

sole. These units are now modified to accept air¬
craft changes specified by T.O. 1F-4D-507 and T.O.
1F-4-702. WRCS operating power is received from
the inertial navigation set (INS) and aircraft power
sources.

The accuracy of the weapons release computer is
directly related to the input parameters received
from the inertial navigation set (INS) and other as¬
sociated systems when employed. The INS accuracy
should be at least maintained at 5.0 nautical miles
of error per hour (CEP). The ground speed indicator
error (while the aircraft is not moving) should not
be greater than 18 knots in 2 hours of navigation
time. However, a higher degree of accuracy can be
obtained which will produce greater bombing ac¬
curacy. The following suggestions are offered.

a. The accuracy of the INS should be maintained at
3 nautical miles of error per hour of CEP by check¬
ing the actual error after each flight and having the
computer gyro bias adjustments made by the ground
crew with the equipment installed in the aircraft.

Even 2 NM/hour of CEP is obtainable.

b. After each flight, the aircrew should note the
ground speed indicator error while the aircraft is not
moving; the indication should not be greater than 8
knots per hour of navigation time.

1-52

Change 6

WEAPONS RELEASE COMPUTER SET/ F-4D

“a*™.*"

dive toss

DIVE /

sP* 3 Bf lAT

to y|HI down

iETT /'WF^ofFSET
1 ^ BOMB

■^-AGM-45

LABS oi
TIMED lEVEl"\

line it om

TIMED LADO-->

TIMED O/S

CURSOR

‘ CONTROL

DISUNCt

’advanci

2 (MiTANtt *

f n»»^ ?

FREEZE * TARGET
INSERT

■ A T
L R
OA

I NC

-* I GK

CROSS TRACK

RESET

. A lTXrWN

OPTICAL SIGHT

STEERING

— SLANT RANGE FROM AN/APQ-109

--ROLL AND

STABILIZATION
SIGNALS
FROM INS

CURSOR

SIGNALS

DELIVERY MODE
SELECTOR PANEL

STEERING

BALLISTIC
COMPUTER
(WRCS COMPUTER)

STEERING

INERTIAL

SIGNALS

AIR-TO-GROUND

RANGE

FRZ, TGT INS CURSOR CONTROL

AGM-45

MISSILE

COMPUTER CONTROL PANEL
(WRCS PANEL)

CURSOR CONTROL PANEL

Figure 1-21

1-53

T.O. 1F-4C-34-1-1

Note

Looseness in the ground speed/ground track
resolver can cause an erroneous readout:
however, the readout is lower than actual and
should not present a problem.

c. The INS double alignment procedure outlined in
flight manual T.O. 1F-4C-1 produces greater WRCS
accuracy.

d. The boresight procedures used by the ground
crew should ensure that the radar boresight line and
the pipper line-of-sight are parallel during the air-
to-ground ranging mode.

e. The hand-set parameters on the WRCS cockpit
panels and the screwdriver adjustments made to the
computer must be accurate.

BALLISTIC COMPUTER, CP-805/ASO-91

The ballistics computer (WRCS computer) is behind
the rear cockpit, door 19. The WRCS computer con¬
tains all of the analog circuitry required to solve the
bombing problem for each WRCS delivery mode.

Built-in-test (BIT) features are incorporated to facil¬
itate a go/no-go check of the WRCS.

The computer has several screwdriver adjustments
(figure 1-20) under the dust cover plate that are
made by the ground crew. These adjustments are
bias factors and should not be confused with the ac¬
tual parameter. For example: V e IS NOT the ejec¬
tion velocity of the bomb in feet per second; V e is
the ejection velocity bias factor that is selected and
applied to the computer. The drag coefficient value
(Cb which is dialed into the computer by the pilot) is
also a bias factor that varies with the type of bomb
and is related to a specific V e bias setting. When V e
is changed, the drag coefficient must be changed.

WEAPONS RELEASE COMPUTER CONTROL PANEL

WRCS MANUAL INPUTS

F-AD

TARGET-FT X100

RELEASE

ALT

RANGE

■■Hm 31

HWtl'l

i$l

□

249

9.99

999

DIVE TOSS

imM

■ V. : ;;

DIVE LAY

IM!!*

□

(§g

TGT FIND

ipflp

iilltii

AGM-45

□

■■

4C—34-34— 1 -1 -(25)

Figure 1-22

west target distance. For the offset bomb and target
find mode, the altitude value placed in the ALT
RANGE control should be either (1) the target or
RIP elevation MSL ± the D value for the planned run
in altitude or (2) the target or RIP pressure altitude.
For the laydown bombing mode, the ALT RANGE
readout control receives the range from the IP to
target in hundreds-of-feet. Either the ALT or
RANGE placard is illuminated under the panel, de¬
pending on the delivery mode selected (red for night
lighting, white for day lighting). The maximum set¬
ting on the target controls is 999 X 100 feet (99, 900
feet). Tick marks are provided on the 100-foot
dial to permit intermediate settings.

The weapons release computer control panel (WRCS
panel) has three TARGET input controls, two RE¬
LEASE input controls, and a bomb DRAG COEFFI¬
CIENT input control. The panel also has a BIT con¬
trol knob that is used to select and test the go/no-go
status of the WRCS. (Refer to figure 1-22 WRCS
manual inputs.)

Target Range Controls

The three target inputs are used for the target find¬
ing mode and the offset bombing mode. The distance
between the IP (identification point) and the target
is placed on the two distance readout displays by ro¬
tating the adjacent control knobs. The distance is
manually placed on the readout control and is in
hundreds-of-feet. The top target distance readout
control receives the north or south distance; the
lower target distance control receives the east or

The dual purpose ALT RANGE control has the follow¬
ing maximum settings: the maximum ALT setting is
100 X 100 feet (10,000 feet); the maximum RANGE
setting is 249 X 100 feet (24,900 feet). The maximum
setting on the N-S and E-W DISTANCE controls is
999 X 100 feet (99, 900 feet).

When a value is inserted on the target ALT
RANGE counter other than 000, do not select
the target finding or offset bombing mode
unless; the aircraft altitude MSL is greater
than the value (times 100) or, performing the
target find/offset bomb WRCS BIT check as
presented in section II. This is necessary to
prevent possible damage to the pitch servo in
the WRCS computer.

1-54

Change 6

T.O. 1F-4C-34-1-1

Release Range Control

Drag Coefficient Control

The release range control knob is used to manually
set the bomb range in tens-of-feet on the digital read¬
out. This control is used for the laydown, dive lay-
down, and offset bombing modes. The maximum
setting is 999 X 10 feet (9,990 feet) when the range
switch on the weapon delivery panel is set on NOR¬
MAL. When the range switch is set on X100, the
maximum setting is 999 X 100 feet (99,900 feet).

Refer to LABS/WRCS Delivery Mode, Weapon De¬
livery Panel, this section.

Note

Do not set the target range control and re¬
lease range control on equal values, allow
at least 0.25 second time/distance between
settings to allow for the maximum possible
bomb rack time delay. If the values are
equal, the bomb may not release or the
, bomb releases late.

RaUas* Advance Control

The release advance control is operative in allWRCS
bomb release modes and in the LABS/WRCS mode.
The release advance control can be used in conjunc¬
tion with the intervalometer on the station and
weapon selection panel to advance the release signal
In milliseconds. For example; if the BOMBS/TRIPLE
mode is selected, with a release interval of 100 mil¬
liseconds (100 MS), the WRCS normally computes the
release of the first bomb-on-target. The release
advance control can be used to place the second bomb
on-target by setting 100 milliseconds on the digital
readout; the first bomb will then hit short of the tar¬
get, the third bomb will hit long of the target. The
counter has a maximum setting of 999 milliseconds.
The release advance setting that will place the mid¬
dle bomb on target can be determined by the following
equation:

For an ODD number of bombs, to place the middle
bomb on target:

The drag coefficient control is used only during the
dive toss mode. The maximum setting is 9.99. The
drag coefficient (Cg) is a bias factor that is analyti¬
cally established to equate the computer bomb tra¬
jectory to the actual bomb trajectory. This drag
coefficient value is not the mathematical drag coef¬
ficient of the bomb. The drag coefficient values and
bias settings are provided in section VI. The ground
crew must set the Ballistic Computer (CP805/ASQ-
91) in door 19. When V e is changed, the drag coef¬
ficient will change.

Built-In-Test (BIT)

The built-in-test (BIT) control is used to establish
the go/no-go status of the WRCS. The BIT selector
knob is not a mode selector switch for computer op¬
eration. The BIT is initiated by rotating the knob to
the bombing mode to be tested and depressing the
button in the center of the selector knob, placarded
PUSH FOR BIT, wait 5 seconds and then depress the
FREEZE button while holding the BIT button de¬
pressed. Upon receiving either a Go or No-Go plac¬
ard illumination, the BIT is discontinued by releas¬
ing the button. The NO-GO (amber) and GO (green)
lights are located under the panel to illuminate the
applicable placard. Illumination of the NO-GO indi¬
cator at times other than the BIT checks indicates
an inertial navigation system malfunction. A NO GO
indication will result if the BIT parameter (listed in
the checklist) are not used. If a NO GO indication is
received as the BIT button is released, the NO GO
indication can be disregarded if a GO indication was
previously obtained. Refer to section II, WRCS BIT
check procedures.

CURSOR CONTROL PANEL

The cursor control panel (figure 1-21) contains the
additional controls required to perform the target¬
finding mode and the offset bombing mode.

Cursor Controls

RA = I R fl?-- !)
rt 2

For an EVEN number of bombs, to place the FIRST
middle bomb on target;

RA -= Ii

(N - 2)

For an EVEN number of bombs, to place the SECOND
middle bomb on target:

ra = i r f

where:

RA = Release Advance Setting in milliseconds.

I R = Release Intervalometer setting in millisec¬
onds.

N-l = The number of bombs released minus one
bomb.

The cursor control panel has two thumbwheel type
cursor controls (or slew controls) placarded ALONG
TRACK and CROSS TRACK. These controls are used
to position the cursors that appear on the AN/APQ-
109 radar scopes when operated in the MAP-PPI
mode. The controls are spring-loaded to return to
the center position after each operation of the con¬
trol; this return motion of the control does not affect
the position of the radar cursors. The along track
control contains a microswitch that activates a relay
to enable the cursor control commands to be re¬
ceived by the WRCS computer. Therefore, the along
track control must be moved first, and then the cross
track control. Until the along track control is moved,
or the FREEZE button is depressed, the velocity in¬
tegrators in the WRCS computer are maintained at
zero distance traveled. The along track control po¬
sitions the range cursor over or below the RIP radar
return. The cross track control positions the vertical
offset cursor over the RIP radar return. The inten¬
sity of the cursors on the scopes can be controlled by

1-55

T.O. 1F-4C-34-1-1

the controls located on scope panel in the rear cock¬
pit. If the cursors appear to be erratic in track or
control, push the reset button and resume operation.

Note

Do not position the range cursor below zero
range. If the range cursor is moved below
zero range and positioned over the IP, the
steering information is in error by 180° and
the cursor responds opposite to along track
cursor control movements.

Freeze Button

When the FREEZE button is energized, the velocity
integrators in the WRCS computer begin to calculate
the distance traveled from zero, and the cursors be¬
gin tracking the ground position indicated on the ra¬
dar scopes by the intersection of the two cursors.

The freeze button remains illuminated until the reset
button is depressed, or until a different delivery
mode is selected. The freeze button is also used
during the BIT check to initiate the test problem for
all bombing modes.

Target Insert Button

When the TARGET INSERT button is energized, the
north-south and east-west distances (entered in the
WRCS panel controls) are inserted into the WRCS
computer. This action causes the cursors to move
from the RIP to the target and begin tracking the tar¬
get location on the radar scope. Only at this point is
target steering information supplied to the various
display instruments. The target insert button re¬
mains illuminated until the reset button is depressed,
or until a different delivery mode is selected.

Reset Button

The reset button is a momentary pushbutton switch
spring-loaded to ON. Depressing the reset button
deenergizes the tracking relays and cause the veloc¬
ity integrators to return to zero distance traveled;
the freeze button light and the target insert button
light go out; the offset cursor on the radar scope
moves to the center of the scope; the range cursor
disappears. The purpose of the reset button is to
permit the aircrew to cancel all previous inputs and
start over. This might be desirable when the RIP can
be visually located and a flyover fix on the RIP ac-

I complished. When the aircraft is directly over the
RIP, the pilot pushes the freeze button to energize
the velocity integrators. If immediate steering in¬
formation is required, the pilot should depress the
target insert button as soon as possible after de¬
pressing the freeze button.

LEAD COMPUTING OPTICAL SIGHT

The lead computing optical sight AN/ASG-22 (figure
J-17) is used to establish a: visual sight reference
for air-to-air and air-to-ground weapons delivery.
The sight unit is mounted on the front cockpit radar
scope. A red reticle image is projected on a com¬

bining glass to serve as the visual sight reference.
The sight can be depressed vertically from zero mils
to 245 mils below the fuselage reference line. The
sight is depressed by rotating the reticle depressing
knob until the digital readout (in one-mil increments)
corresponds to the desired sight setting. The sight
cannot be manually positioned in azimuth.

Power is applied to the lead computing sight compo¬
nents and the gyroscope when the sight mode selector
knob is in any position except OFF. In STBY, the
sight reticle is mechanically caged, but not illumi¬
nated. In CAGE, the sight reticle is illuminated and
mechanically caged to the radar boresight line. The
radar boresight line is located 35 mils below the
fuselage reference line; therefore, the optical sight
setting is 35 mils, regardless of the reticle depres¬
sion knob setting. The optical sight is mechanically
caged when the sight mode selector knob is positioned
to OFF, STBY, or CAGE. The optical sight has two
modes of operation that are selected by the position
of the mode selector knob located on the front cock¬
pit scope panel: A/G (air-to-ground) and A/A (air-
to-air). Variations of the two basic modes are con¬
trolled by the position of the weapon selector knob on
the pedestal panel and the position of the selector
knob on the delivery mode selector panel. Refer to
figure 1-23 for the description of the optical sight
functions with the various delivery modes, and refer
to F-4D Weapon Delivery Modes, this section.

The reticle image that is projected on the combining
glass is composed of a fixed reticle, roll reference
tabs, and a range bar (figure 1-24). The fixed reticle
consists of a two-mil diameter pipper located in the
center of a 25-mil diameter segmented circle, and a
50-mil diameter complete circle. The 50-mile circle
has three index tabs located on the outer edge at the
top, and left and right of the pipper.

The roll reference tabs rotate about the 50-mil
circle. The roll reference tabs have two separate
functions. During the offset bombing mode and the
target finding mode, the roll tabs provide steering
information supplied by the WRCS. The position of
the roll tabs, with respect to the fixed index tabs,
indicates the angle between the ground track and
course to the target. During all other modes of op¬
eration, the roll tabs indicate the aircraft roll atti¬
tude which is supplied by the INS.

The sight reticle flashes on and off to indicate a mal¬
function in the INS. When the INS is malfunctioned,
the weapon release computer is inoperative. If the
INS is inoperative, the DIRECT bombing mode should
be used. The sight will also flash when the bomb re¬
lease button is released prior to bomb release, indi¬
cating an aborted run or no WRCS solution. The
bomb button cannot be re-depressed to continue the
bomb run - the bomb run is aborted, except for the
offset bombing mode. The only requirement for the
offset bombing mode is that the bomb button be de¬
pressed at the time the bomb release signal is gen¬
erated.

1-56

999 9 9

T.O. 1F-4C-34-1-1

OPTICAL SIGHT FUNCTIONS

DESIRED

WEAPON

DELIVERY

MODE

SIGHT

MODE

SELECTOR

KNOB

OPTICAL SIGHT RETICLE

DELIVERY

SELECTOR

KNOB

SELECTOR

ELEVATION

AZIMUTH

ROLL TABS

RANGE

BAR

Guns A/A

D NA

A/A

Lead

Compute

Lead

Compute

Roll

Max Range
6700 ft

Guns A/G

GUNS

OFF

DIRECT

A/G

Manual Dep.
from FRL

Caged
at 0°

Rockets

RKTS &

DISP

A/G

Manual Dep.
from FRL

Caged
at 0°

■i

Tgt. Find

TGT FIND

A/G

Caged at

RBL

Caged
at 0°

Dive

Toss

DIVE TOSS

A/G

Caged at

RBL

Drift

Roll

Dive

Laydown

E> NA

DIVE LAY

A/G

Caged at

RBL

Drift

Roll

Laydown

O NA

LAYDOWN

A/G

Drift

Roll

Offset Bomb

D NA

OFFSET

BOMB

A/G

Caged at

RBL

f»

Max Range

6700 ft
(*20,000
feet).

TIMED LEVEL,
TIMED LADD,
TIMED O/S,
LOFT, or

INST O/S

A/G

Caged
at 0°

Roll

Direct

Bombing

BOMBS or
RKTS & DISP

DIRECT

A/G

Manual Dep.
from FRL

Caged
ot 0°

Roll

AGM-12 or
AGM-62

A/G

Manual Dep.
from FRL

Roll

AGM-45

A/G

Caged at

RBL

Caged
at 0°

Roll

Missiles
Air- to-Air

I^OFF

A/A

Caged at

RBL

Caged
at O’

Roll

RBL = Radar Boresight Line FRL = Fuselage Reference Line. NA = Not Applicable.

The lead computing function of the optical sight reticle is not altered by the delivery mode selector panel section, nor by the selec¬
tion of GUNS & STORES. The master arm switch must be in ARM. (*When the ARR button is held depressed, the lead angle computer
receives a fixed 1500-foot range signal; the range bar continues to indicate the actual slant range, or maximum dlsplayable range of
6700 feet.)

The roll tabs display roll attitude until Target Insert, then the roll tabs display steering commands to the target.

The sight reticle is pitch stabilized; manual depression is from the level plane (the local horizontal). If INS fails, sight depression
will be in error by the amount of the pitch angle at the time of INS failure.

Only DIRECT position can be used to fire rockets.

The function of the optical sight depends upon the delivery mode selector panel selection (except for GUNS).

The OFF position should be selected; however AIM missiles can be launched with any position selected except LABS. The function
of the optical sight is not affected when air-to-air mode is selected.

If weapon selector knob is in GUNS, the sight functions as a combination of the delivery mode selected and GUNS A/G.

If GUNS (or GUNS & STORES) is selected, the master arm switch must be in SAFE to launch air-to-air missiles.

* T.O. 1F-4D-514

Figure 1-23

4C-34-1-1—(26)

Change 4

1-57

OPTICAL SIGHT RETICLES] F-4D

RANGE BAR FUNCTION

2 MIL

DIAMETER
PIPPER |-

-25 MIL DIAMETER
SEGMENTED CIRCLE

50 MIL
DIAMETER
CIRCLE -

FIXED RETICLE

FIXED INDEX
TABS

EFFECTIVE ON_
SOME F-4D AIRCRAFT

RANGE

* WINGS LEVEL
* *(OR ON COURSE)

«».. * RIGHT ROLL * LEFT ROLL

**(0R STEER LEFT) * *(0R STEER RIGHT)

*'* STEERING COMMANDS FOR TARGET FINDING OR OFFSET BOMBING MODES.

* AIRCRAFT ATTITUDE

AFTER RADAR LOCK-ON
Max ranee 20,000 FT
triple tanging when guns A/A is not
selected; alter Incorporation of T.O.

AFTER RADAR LOCK-ON
Max range 6,667 FT
with guns A/A selected.

BEFORE RADAR LOCK-ON

1F-4D-614 and Block 32 and up.

Figure 1-24

1-58

Change 2

T.O. 1F-4C-34-1-1

The range bar is semi- circular and appears on the
inside of the 50-mil circle only when a target has
been acquired by radar lock-on. The instantaneous
length of the range bar, and the rate at which the
length is changing indicates the actual radar slant
range and the range rate between the aircraft and the
target. The length of the range bar can be 170°, be¬
ginning at the 6 o'clock position. When the inside
tab on the range bar is at the 6 o’clock position, the
actual radar range is 1000 feet. When the range bar
tab is at the 5 o'clock position the range is 2000 feet.
The range indication is linear; i.e., 1000 feet per
each number on the face of a clock. When the range
bar reaches its maximum length, (near the 12 o'clock
position), the radar range is 6667 feet. If the range
is greater than 6667 feet, the range bar will remain
at the maximum position. Refer to Range Bar Triple
Ranging. The range bar appears on the sight reticle
to indicate the slant range to the target when radar
lock-on is accomplished:

a. With the mode switch in A/A, the range bar ap¬
pears when radar lock-on is accomplished in any of
the radar modes and indicates slant range to the tar¬
get for air-to-air gunnery and air-to-air missile at¬
tack. (Refer to Air-to-Air Gunnery.)

b. With the mode switch in A/G and the DIVE TOSS
or DIVE LAY mode selected on the delivery mode
selector panel, the range bar will appear to indicate
radar lock-on has been accomplished in any of the
radar modes and will indicate slant range from the
aircraft to the position of the pipper on the ground.

RETICLE CAGING MODE

(AFTER T.O. 1F-4D-514).

In the guns lead compute mode of the optical sight,
the ARR button may be depressed to energize a
reticle stiffness relay in the computing amplifier
(figure 1-25). With radar lockon, the sight reticle
moves in azimuth and elevation to display the lead
angle required. Before radar lockon a pseudo-range
of 1500 feet is supplied to the lead angle computer;
the range bar is not displayed. After radar lockon,
the actual slant range to the target is supplied to the
computer and displayed by the range bar. When
lockon is accomplished out of gun range, the sight
reticle may be over sensitive due to the range, high
G forces and/or constant maneuvering flight. The
sensitivity of the reticle can be reduced by depress¬
ing and holding the ARR button. When the ARR button
is held depressed, the lead angle computer receives
a fixed 1500-foot range signal; the range bar contin¬
ues to indicate the actual slant range or the maxi¬
mum displayable range of 6700 feet. When the trig¬
ger transfer relay is energized by selecting guns,
the function of the ARR button is also transferred to
provide reticle caging. The missile arm switch and
missile select switch may be in any position; the
AIM-4D coolant supply is not activated.

RANGE BAR TRIPLE RANGING

Interpretation of the slant range displayed by the po¬
sition (or length) of the range bar is affected only

when guns air-to-air is selected. With GUNS A/A
selected, the minimum length of the range bar rep¬
resents 1000 feet and the maximum length represents
6667 feet (approximately 6700 ft). When any other
weapon or delivery mode is selected, the minimum
length of the range bar represents 3000 and the max¬
imum length represents 20, 000 feet.

LOFT BOMBING EQUIPMENT
CONTROLS

The loft bombing delivery mode utilizes the following
controls and indicators (figure 1-17).

a. Attitude director indicator (ADI).

b. Accelerometer.

c. Pullup light.

d. Bomb release angle computer (Low Angle).

e. Bombing timer (Pullup Timer).

f. Delivery mode selector knob.

g. Pedestal panel.

h. Bomb release button (pickle button).

The following describes the controls as they are uti¬
lized to perform the loft delivery mode. Only the
function of the controls which have not been described
elsewhere will be discussed here.

ATTITUDE DIRECTOR INDICATOR (ADI)

The ADI aids the AC in establishing and maintaining
a constant G pullup maneuver. The pointers are pro¬
grammed to move out of center when the aircraft is
not following the programmed pullup profile of 4.0
G's obtained in 2 seconds and maintained thereafter,
and a wings-level pullup. When the loft bombing
mode is performed by using a pullup acceleration of
3.0 G's obtained in 2 seconds, the ADI should not be
used; use the aircraft accelerometer.

When the bomb button is depressed, the vertical
pointer centers — preventing the roll signal and indi¬
cating flight path deviations while the pullup timer is
operating. At pullup, when the pullup timer is com¬
plete, the resolved yaw/roll signal is presented on
the vertical pointer. If the pointer deflects to the
right during the pullup, the AC rolls to the right—
correcting into the pointer. The vertical director
warning flag appears or disappears to indicate the
degree of TACAN signal strength. Therefore, the
appearance of the flag has no meaning with respect
to the vertical pointer in a bombing mode.

Note

For LOFT mode of LABS delivery, the
pedestal panel REJECT switch should be in
DF REJ, or else the weapon selector must
not be in the AGM-45 mode. This is neces¬
sary to get the ADI vertical pointer into the
LOFT yaw/roll network.

Change 6

1-59

T.O. 1F-4C-34-1-1

The horizontal pointer is always deflected out of view
unless the loft bomb run is in progress (bomb button
depressed). The pointer indicates deviations in the
1.0 G flight path during the low level approach to the
pullup point. When the pullup timer is complete,
horizontal pointer movement represents error be¬
tween the desired pullup G program and actual load
factor which is measured by the accelerometer. Note
that the system actually programs the proper G
build-up rate, which means that if the AC increases
G loading at the proper rate, the pointer will never
move from the center of the sphere. The pointer
continues showing error in the constant 4.0 G flight
path until the AC releases the bomb button after final
bomb release.

The ADI OFF flag comes into view if: (1) a system
ac or dc power failure occurs; (2) there is excessive
error in the roll and pitch signal sources of the gyro¬
scope assembly; (3) an ADI failure, or an internal dc
failure within the ADI occurs. The OFF flag indi¬
cates malfunctions of the ARBCS only, regardless of
the mode the AC has selected (PRIM or STBY) on the
compass control panel. If the gyro system fails in
some manner (as suggested by conditions 1 and 2
above), the aircrew cannot expect to obtain an accu¬
rate bomb release angle, since release occurs
through the ARBCS pitch following system.

BOMB RELEASE ANGLE COMPUTER

The release angle computer contains the high and low
angle release switches, the drum shaft and yaw/roll
resolver, and the drogue switch. The pitch inputs
drive the drum shaft which actuates the high and low
angle release switches. The yaw and roll inputs are
resolved, as a function of pitch, and transmitted to
the flight director bombing computer for use in the
vertical director pointer network. The controls on
the front of the computer are available in the rear
cockpit. The Low Angle control may be set from 0°
to 89.9°, and the High Angle control may be set from
70° to 179.9°. Only the Low Angle control is used for
loft bombing.

WARNING

When the LABS release angle gyro is set
greater than 169.0°, bomb release may occur
at the pullup point when the bomb button is
depressed (INST O/S) or at the completion
of the Pull Up Bombing Timer (TIMED O/S).

FLIGHT DIRECTOR BOMBING COMPUTER

The flight director computer contains a roll cancel
relay which is energized if roll error (yaw/heading

Change 6

change) exceeds 30° during the pullup flight path.

With the roll cancel circuit energized, the release
circuit cannot be energized and the bomb run is can¬
celled. To ready the system for another run, mo¬
mentarily position the delivery mode selector knob
out of the selected function then back to LOFT.

BOMBING TIMER (DUAL TIMER)

The dual timer controls include the pullup and release
timer controls in the rear cockpit. The pullup timer
may be set from 0 to 60 seconds and the release
timer may be set from 0 to 30 seconds. Both timers
are settable in increments of 0.1 seconds with 0.1
seconds as the minimum numerical setting. The set¬
ting references in the window do not move during the
application of operate voltage in the bomb run. Com¬
pletion of the pullup timer energizes relays which
provide the various pullup signals and the pullup
flight program. The timers are either motor driven
or solid state. The motor driven timer receives 115
volt ac power; the solid state timer receives 28 volt
dc. Timer excitation voltage is applied when the AC
selects any LABS mode except DIRECT. Timer ini¬
tiate (operate) voltage is applied, however, as a
function of the specific mode selected. To demon¬
strate, the following list summarizes the timer op¬
erated versus the mode selected. (Operate voltage
is applied by actuating the bomb button.)

a. LOFT, TIMED O/S-

b. TIMED LEVEL and TIMED LADD

Operate voltage is applied to the PULLUP
timer; then to RELEASE timer at the termina¬
tion of the PULLUP timer countdown. For the
LADD mode, the PULLUP timer must be set
on some value to get the ADI pullup schedule;
the RELEASE timer must be set to develop a
bomb release signal.

c. INST O/S-

Operate voltage is not applied to either timer.

d. Pullup Warning Tone-

(1) Motor Driven Timer: For all modes in which
the PULLUP timer is set, a 0.25 second
warning tone pulse is initiated 1 second prior
to PULLUP timer completion.

(2) Solid State Timer: A warning tone pulse is
not provided.

For LABS/WRCS modes of operation, the above in¬
formation remains the same except that the tinier
operate signal is applied by a signal from the WRCS
ACTIVATE circuits, rather than the bomb button.

In all LABS/WRCS combined modes, a 0.375 second
activate tone is applied at the ACTIVATE point.

Note

The pullup tone to the head set will transmit
over the air unless the function selector knob
on the communication control panel is placed
in the STBY position, or the pullup tone cut¬
off switch is positioned to TONE OFF (refer
to Pullup Tone Cutoff Switch).

1-60

T.O. 1F-4C-34-1-1

WEAPON DELIVERY MODES (F-4D)

AIR-TO-AIR GUNNERY

The following aircraft equipment comprise the F-4D
air-to-air gunnery capability:

a. SUU-16/A, -23A Gun Pod.

b. AN/ASG-22 Lead Computing Optical Sight System
(LCOSS).

The aircraft systems listed below are electrically
interfaced with the optical sight system in support of
the air-to-air lead computing mode.

a. AN/ASN-63 Inertial Navigation Set.

b. A24G-34 Air Data Computer Set.

c. AN/APQ-109 Radar Set.

In the lead computing mode, the sight system solves
for a predicted point of impact by developing a solu¬
tion to the vector diagram shown in the upper part of
figure 1-25. The solution is computed in terms of
aircraft azimuth and elevation coordinates, not earth
coordinates. The net az-el solution is a function of
trajectory shift, gravity drop, and kinematic lead
vectors. The resultant is the lead angle, which is the
angle formed between the gun bore line and the pipper
sight line with the pipper on target. The vectors are
briefly defined below.

Chang e 3

1-61

T.O. 1F-4C-34-1-1

TRAJECTORY SHIFT

Trajectory shift occurs because the gun bore line and
the aircraft flight path are not the same. The line of
departure of the bullets therefore forms an interme¬
diate path which is a function of the gun muzzle veloc¬
ity vector, the aircraft flight path vector, and the in¬
cluded angle. Since trajectory shift lies in the pitch
plane of the aircraft, the sight gyro system is cali¬
brated (a fixed setting for each altitude and range)
to correct for trajectory shift in the elevation net¬
work.

GRAVITY DROP

Gravity drop is a function of bullet time of flight and
the force of gravity. A correction for gravity is also
applied by a fixed calibration to circuits of the lead
computing gyro. In maneuvering flight, the compo¬
nents of gravity lie in both the azimuth and elevation
planes. Therefore, the calibration effects the az-el
network.

KINEMATIC LEAD

The kinematic portion of the problem involves lead
computations which compensate for the continuous
change in position (or motion) between the target and
the interceptor. This portion of the vector diagram
lies in a plane which includes the velocity vector of
the target and the position of the interceptor. The
computation is a direct function of the motion of the
interceptor in the pitch (elevation) and yaw (azimuth)
planes. The az-el gyro output is in turn influenced in
magnitude by radar range, air density, and accelera¬
tion signals (figure 1-25). Considering the flow dia¬
gram, the gyro magnet axis is fixed and lies parallel
to the radar boresight line (RBL). In maneuvering
flight, the magnet axis follows RBL while gyro re¬
sists any change in direction. Since the gyro dome
rotates directly in the magnetic field, an increase or
decrease in magnet current strength has a sensitivity
(precession) effect on the position of the gyro. For
example, an increase in magnet current strength -
which occurs with a decrease in radar range - causes
the gyro spin axis to precess and align more closely
with magnet axis. The resultant gyro motion, which
is transmitted to the optical sight reticle, becomes a
reduction in the indicated azimuth and elevation lead
as the aircraft closes with the target.

Compensations for acceleration are accomplished in
a similar manner as described above. Current flow
in the accelerometer network applies a restraining
force to the gyro gimbal, which in turn causes the
gyroscope to precess in elevation and increases gyro
sensitivity. Hence, an increase in normal accelera¬
tion causes an increase in the indicated elevation
lead angle.

cal sight corrections are these plus the calibrations
for gravity drop and trajectory shift.

As the flow diagram shows, the sight system provides
lead data for the constant 1500 foot range when radar
lockon is lost or when the AC actuates electrical
cage. With radar lockon, range data is always avail¬
able to the reticle range bar when range is within the
limits of 900 and 6700 feet. However, the sight com¬
putes lead for a maximum range of 4000 feet. Roll
reticle signals are applied directly from the INS gyro
platform.

In a typical lead pursuit firing pass, the position of
the pipper on the combining glass is of little impor¬
tance while the aircraft is well outside the tracking
range. For any one set of maneuvering conditions,
the greater the range, the greater the instability of
the sight reticle. Hence, the ARR button may be held
depressed until the AC can reach a tracking range
(4000 feet or less). The most important single factor
which the AC must properly control is aircraft accel¬
eration. As the AC tracks and pulls the pipper (from
a point aft of the target) up into the target, accelera¬
tion build-up rate should be constant. Then the act
of stabilizing the pipper on target is a matter of hold¬
ing a G that has already been obtained, and for which
the sight has already compensated.

The air-to-air gunnery mode is selected by placing
the delivery mode selector knob to OFF (or as de¬
sired), the weapon selector knob on GUNS, and the
optical sight mode knob on A/A. The radar is oper¬
ated in the RDR or MAP-B modes and in the AI
ranges (normally, Rl) where lock-on and automatic
tracking are possible. Prior to the attack, the guns
and stores switch is in NORMAL, the guns AUTO-
CLEAR or NONCLEAR position is selected, the ap¬
plicable station selector buttons are pushed ON, and
the master arm switch is placed to ARM. Both the
peen SELECTED light and amber READY light with¬
in the selector button must be illuminated before the
guns can be fired.

The gun pod can be carried on the outboard armament
pylons and on the centerline bomb rack. The gun
pods are boresighted along the fuselage reference
line and harmonized to converge at 2250 feet. The
specified accuracy of the SUU-16/A -23/A gun pod
with the M61A1 gun is 80 percent dispersion within
an 8 mil cone. Part IV illustrates the harmonization
range and dispersion cone for 80 percent of the
rounds fired at minimum and maximum range.

Note

Refer to Air Refueling Release (ARR) Button
(reticle caging mode) and to Automatic Ac¬
quisition Switch, this section.

DIRECT DELIVERY MODE

When the DIRECT position on the delivery mode se¬
lector panel is selected, the bomb release button is
in direct control of the bomb release relay. The
DIRECT position must be used to fire rocket launch¬
ers. Depressing the bomb release button releases

1-62

T.O. 1F-4C-34-1-1

OPTICAL SIGHT SIGNAL PLOW I F-4D j

MODE

| EARTH 1
| VERTICAL jgj

Notes

LEAD L_
ANGLE!

GYRO MAGNET CURRENT STRENGTH IS A FUNCTION OF SUMMED
RADAR RANGE AND AIR DENSITY SIGNAL INPUTS.

AZIMUTH LEAD OUTPUT IS A FUNCTION OF AIRCRAFT YAW
RATE. THE MAGNITUDE OF AZIMUTH OUTPUT IS CONTROLLED
BY MAGNET CURRENT STRENGTH.

ELEVATION LEAD OUTPUT IS A FUNCTION OF AIRCRAFT PITCH
RATE. THE MAGNITUDE OF ELEVATION OUTPUT IS CONTROLL¬
ED BY ACCELEROMETER OUTPUT AND MAGNET CURRENT
STRENGTH.

MECHANICAL CONNECTION

GUN BORE LINE

TRAJECTORY SHIFT | f i

GRAVITY DROP

ELEVATION

LEAD

KINEMATIC LEAD

SIGHT
PIPPER ON
TARGET

AZIMUTH

LEAD

ELECTRICAL CONNECTION

LEAD COMPUTING OPTICAL SIGHT AN/ASG-22

OPTICAL DISPLAY UNIT

SELECT

GUNS

pedestal!
PANEL |

RETICLE

STIFFNESS

RELAY

MODE SWITCH ROLL RETICLE

ROLL f;
RETICLE •:
DRIVE UNITS L

RETICLE

CAGE

ENERGIZED AT
RADAR LOCKON

1500 FT.
RANGE
NETWORI

RANGE BAR
DRIVE UNITS

ARR BUTTON
(CONTROL
STICK!

LEAD COMPUTING GYROSCOPE

RANGE

RETICLE

RADAR

RANGE

ENERGIZED
AT RADAR
LOCKON

AZIMUTH

XMTR

NETWORK

azimuth;

DRIVE
UNITS ;

AZIMUTH LEAD

GYRO MOTOR

GYRO

FRAME

SERVOED

MIRROR

^COMPUTER
l SET

t * ■ ELEVATION

GYRO MAGNET XMTR

MAGNETIC

CURRENT

MAGNETIC

CURRENT

SUPPLY

ELEVATION

DRIVE

UNITS

Figure 1-25

1-63

UNCLASSIFIED

T.O. 1F-4C-34-1-1

the bombs, fires rockets or launches the air-to-ground
missiles from the selected stations. The direct de¬
livery mode requires that the preplanned release
parameters for the mission be established and con¬
trolled by the aircrew; the WRCS is not used. The
air-to-ground mode of the optical sight establishes
the bomb release point for a given release altitude,
release airspeed, and dive angle.

DIVE TOSS BOMBING MODE

The WRCS dive toss bombing mode is a visual deliv¬
ery mode used to deliver the low drag bombs. Since
preplanned release parameters are not required, the
target may be approached from any direction, air¬
speed, and dive angle. The bomb will be automati¬
cally released when the bomb trajectory intercepts
the target. Figures 1-13 and 1-14 illustrate the var¬
ious delivery maneuvers that can be used with the
dive toss mode: dive-level, dive-glide, or dive-toss.
This manual presently contains the data required
(drag coefficients) to deliver bombs using the dive-
toss bombing mode. Refer to section VI, Drag Co¬
efficients.

The AN/APQ-109 radar set is operated in the AER-
GRD mode and in the R1 range to provide a drift
stabilized, boresighted antenna. The radar supplies
slant range information to the WRCS computer and
the optical sight. The lead computing optical sight is
used to visually establish a radar fix on the target.

The sight is operated in the air-to-ground mode to
provide roll reticle display and provide a sight reti¬
cle which is electrically caged in elevation to the
radar boresight line (depressed 35 mils from the
fuselage reference line) and drift stabilized in azi¬
muth. The dive toss bombing mode is selected by
placing the delivery mode selector knob to DIVE
TOSS and positioning the weapon selector knob to
BOMBS/REPPLE, TRIPLE, or SINGLE. The only
controls used on the WRCS panel are the drag coef¬
ficient control and, if required, the release advance
control. Use of the R2 and R3 range is not recom¬
mended since the position of the ground return line
sometimes causes inadvertent side lobe lockon.

Note

With the weapon selector knob in any position
other than BOMBS-SINGLE, TRIPLE, or
RIPPLE, the sight depresses according to
MIL setting causing a gross error.

After the target area has been visually identified, the
AC begins to dive toward the target. The slant range
(roll in altitude) is normally 20 percent higher than it
would be for direct dive delivery to allow time for
the accomplishment of air-to-ground lock-on by the
pilot. Target tracking is not required prior to radar
lock-on, i.e., the objective is to maneuver the air¬
craft to obtain a strong ground return on the radar
scope which the pilot will use to obtain a lock-on.

During the initial lock-on attempt, the all important
factor in obtaining a lock-on that will hold until after
PLMS and after depressing the bomb button, is a
CONSTANT range rate. For example, constant range
rate is attained when the dive angle is constant and
there is no rapid movement of the nose attitude.

Lock-on is broken by a RAPID CHANGE in range
rate. Lock-on can be obtained while inverted if the
range rate can be maintained constant. However, a
RAPID CHANGE in range rate during the roll-out
may cause the radar to break lock-on; this is espe¬
cially true prior to PLMS. After PLMS, the aircraft
can be maneuvered with a higher range rate change
without loosing lock. PLMS cannot occur until after
the 2-second time delay has elapsed. Tfie range
strobe may wander up and down the clutter while
seeking the center of the radar beam. The range
strobe must be tracking at a constant rate before
reliable slant range will be available when the AC
depresses the bomb button. The 2-second time delay
is initiated when range lock-on is obtained.

Note

On radar sets modified by T.O. 12P2-

2APQ109-533, PLMS occurs approximately

0.5 second after lockon.

Lock-on should be monitored by the angle lock light
if the manual V c knob is pushed on to close the angle
lock switch. The angle lock light illuminates immed¬
iately after range lock is obtained and goes out im¬
mediately when range lock (or angle lock) is broken,
even when the range track circuit is operating on the
5-second memory circuit. The range bar and the
lock-on display are retained during the memory time.
The 5-second memory circuit is not available until
after the 2-second time delay has elapsed; this will
normally occur just prior to or at PLMS. If the sys¬
tem goes on memory, (angle lock light out) the pilot
should break lock-on and reaccomplish lock-on while
the range rate is constant. The bomb button should
not be depressed while the system is on memory be¬
cause the memory circuit may contain a rapid range
rate that will drive the range gate toward zero slant
range. This could cause the bomb to be released
short of target; release might occur when the bomb
button is depressed. After PLMS the aircraft can be
maneuvered for the final phase of the dive toss de¬
livery; mild changes in range rate should not cause
the radar to break lock-on after PLMS has occurred.
The pilot should observe the angle lock light is on to
ensure that the memory tracking circuit is not being
employed and inform the AC that a valid range lock
is available.

The AC must maintain a constant range rate during
the lock-on phase (prior to PLMS) and for at least
1-second prior to depressing the bomb release button.
The bomb release button should not be depressed until
after the pilot has confirmed a valid lock-on. The
range rate can be observed by the movement of the
pipper on the ground: the pipper should be moving
toward the target at a constant rate. When the pipper
is on target, the AC depresses the bomb button to
insert the slant range between the aircraft and the
target at that instant. After depressing the bomb
button the AC begins desired delivery maneuver while
maintaining a wings-level ground track that will pass
through the target. Radar lock-on is not required
after the bomb button is depressed since the slant
range input is terminated when the bomb button is
depressed.

1-64

T.O. 1F-4C-34-1-1

Note

To ensure that the bomb button is not de¬
pressed at the initiation of the pull-up maneuver
(or dive maneuver), the AC should follow
through after depressing the bomb button by
maintaining the constant range rate for a
short period after depressing the bomb button.

* If it is apparent that the drift stabilization
portion of the sight is malfunctioning, a de¬
livery can be accomplished with the sight
caged and an estimated wind correction off¬
set aimpoint used.

The radar range may be greater than the maximum
range display capability of the range bar, thus, the
maximum length of the range bar will be displayed.
Observe the range bar for a false tracking indication.
If a rapid decrease in range is displayed, the pilot
may have locked on a radar side lobe rather than the
main radar beam. Immediately request the pilot to
break-lock for another attempt.

Regarding the dive toss bombing mode, the aircrew
must consider the computer limitations. The bomb but¬
ton signal may be delivered at a maximum slant ranges
of 25, 000 feet, and at a maximum altitude of ap¬
proximately 18, 000 feet AGL. A profile in section
IV shows expected computer accuracy within these
parameters. The profile considers only computer
accuracy, and that computer inputs from all other
systems are within specified limits.

After the bomb button is depressed, the AC begins
the desired delivery maneuver: dive-level, dive-
glide, or dive-toss. The vertical needle on the ADI
will display deviations from the magnetic heading
established at pickle. The dive-toss maneuver con¬
sists of a pullup maneuver (at the desired acceleration
rate) that is initiated after depressing the bomb but¬
ton. The climb angle must not be greater than 10°
before release to ensure the accuracy of the bomb
release point. The AC should strive for a straight-
line ground track through the target. The roll tabs
on the sight reticle will assist the AC in maintaining
a wings-level dive and pullup. The bomb release
button must be depressed (and held depressed until
bomb release) when pipper is on or slowly passing
through the target. The dive-glide maneuver consists
of a shallow dive toward the target until bomb release
occurs. For example: if the initial dive angle was
40° when the bomb button was depressed, the dive
must be decreased by a minimum of 5° (40° -5° = 35°)
for low drag bombs. If the initial dive was 30°, then

the dive-glide maneuver must be a 20° dive or (30°
-10° = 20°). The dive-level maneuver consists of a
level flight approach toward the target until bomb
release occurs. The dive-toss, dive-glide, and the
dive-level maneuvers are illustrated in figure 1-26.
The WRCS function and requirements are the same
as for the dive toss maneuver. The requirements of
the dive-glide and dive-level maneuvers are:

a. The bomb release button is normally depressed
when the aircraft is at a greater slant range from the
target than is required for the dive-toss maneuver.

b. The aircraft will maintain a wings-level flight
(after depressing the bomb button) for a longer period
than is required for the dive-toss maneuver.

When the AC depresses the bomb release button, the
position and attitude of the aircraft, with respect to
the target, is set into the weapons release computer.
The slant range to the target, obtained by the AN/
APQ-159 radar, is resolved with inputs from the INS
to establish the ground range and altitude above the
target. The weapons release computer begins to
integrate ground speed and subtract the results from
the initial ground range. Vertical velocity is also
integrated and the results are subtracted from the
initial altitude above target. The weapon release
computer continuously monitors the aircraft altitude
and ground speed and automatically supplies a release
signal when the computer trajectory of the bomb in¬
tersects the target.

AIR-TO-GROUND LOCK-ON

The AIR-GRD radar mode is used only for the dive
toss and dive laydown bombing modes. The purpose
of the radar AIR-GRD mode is to establish the slant
range to the target and route this range data to the
WRCS. The WRCS then computes the position of the
aircraft with respect to the target and automatically
releases the bomb when the target is within bombing
range.

Prior to the bombing run, the AC selects one of the
dive delivery modes on the delivery mode selector
panel, selects the A/G optical sight mode, and pre¬
pares the pedestal panel for a weapon release. The
pilot places the radar power switch to OPR, the radar
range switch to R1 and the radar mode switch to
AIR-GRD. The radar antenna and the optical sight
are now drift stabilized; the optical sight line is par¬
allel with the radar boresight line (the centerline of
the radar beam). The B-sweep (and range strobe) is
offset from the center of the scope equal to the drift
angle.

Change 1

1-65

T.O. 1F-4C-34-1-1

dlVl TOSS BOMBING MODE I F-4D I >iSS

STATION «. WEAPON SEIEC

outer.

MASTER

ARM

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OPTICAL SIGHT:

1. Drift Stabilized

2. Reticle caged to the
radar boresight line.

VISUALLY TRACK
TARGET MOMENTARILY

WRCS Manual Inputs:

1. Drag coefficient (not set less

2. Release Advance.

AUTOMATIC BOMB
RELEASE-1

DEPRESS AND
HOLD BOMB
RELEASE BUTTON

AN/APQ-109 MODE:

1. A/G

2. Rl or R2 Range

RELEASE BOMB
BUTTON AND
INITIATE ESCAPE

INS Supplies:

1. Groundspeed

2. Pitch Angle

3. Vertical Velocity

PIPPER SIGHT LINE
AND RADAR ANTENNA
BORESIGHT CENTERLINE

RADAR CONICAL
SCAN PATTERN

TARGET

BOMB

RELEASE

SIGNAL

DELIVERY MODE
SELECTOR PANEL!

INERTIAL

NAVIGATION

SET

GROUND SPEED.
PITCH ANGLE.
VERTICAL
VELOCITY

WEAPON AND STATION
SELECT PANEL

AN/APQ-109

AIR-TO-GROUND

MODE

COMPUTER

WRCS CONTROL PANEL

OPTICAL SIGHT
AIR-TO-GROUND MODE

F4D-34-1-214-1

Figure 1-26 (Sheet 1 of 2)

1-66

Change 1

T.O. 1F-4C-34-1-1

DEPRESS BOMB BUTTON
AND INCREASE DIVE ANGLE

MAINTAIN THE
GROUND TRACK
THROUGH THE
TARGET

/ / f f / / t / / / / f /

/ / ' / / / / / / / / /VC

/ / ‘ I / ill 1 / /

/ / / / / / JARGET/ /xf /

j I ' I /CENTER xT / / ,

-LEVEL APPROACH
TO THE TARGET

l— AUTOMATIC ADVANCED
BOMB RELEASE

• PIPPER AND RADAR CENTERLINE

F4D-34-I-214-2

Figure 1-26 (Sheet 2 of 2)

1-67

T.O. 1F-4C-34-1-1

The gain should be reduced until the length of the
ground return in the B-sweep is as short as possible
before the return begins to break up and fade. The
fine adjustment knob on the receiver gain control will
aid the pilot in this task. The actual length of the re¬
turn is a function of the antenna graze angle (aircraft
dive angle) and the amount of receiver gain. For a
25° dive angle, the main beam clutter band can be
reduced to approximately 1/2-mile long. The clutter
band is longer for the lower dive angles. The center
of the main beam clutter band displayed on the scope
is the point on the ground receiving the highest con¬
centration of energy - the center of the radar beam.
This is also the point on the ground seen by the AC
through the optical sight pipper position.

Adjust the receiver gain until the smallest amount of
clutter is present. The acquisition symbol should be
positioned at approximately 4 miles and lock-on
should not be attempted until the clutter is in this
area. Then depress the action switch to Half-Action.
The range strobe will then appear between the ac¬
quisition symbol. Slant range is supplied to the com¬
puter when the range strobe is on the scope. Move
the hand control to position the range strobe directly
in the center of the main beam clutter band; then de¬
press the action switch to Full-Action to obtain radar
lock-on.

After lock-on, range tracking is announced by the
appearance of the ASE circle on both scopes, illumi¬
nation of the angle lock light, and the appearance of
the range bar on the sight reticle; the acquisition
symbol is removed. Approximately 2 seconds after
lock-on, power level mode switching (PLMS) occurs;
the ground return is sharply reduced allowing only
the range strobe to appear. The slant range input is
more accurate after PLMS.

Note

The lock-on should not be considered valid
until after PLMS and the range tracking cir¬
cuit is not operating on memory.

Slant range can be interpolated by the vertical posi¬
tion of the range strobe which moves down the
B-sweep display as the slant range to the target de¬
creases. The ASE circle remains in the center of
the scope and fixed in diameter.

Another consideration to ensure bombing accuracy is
the stability of the range strobe. The range strobe
may wander up and down after lock-on for 2 to 3 sec¬
onds prior to power level mode switching (PLMS).

The range strobe must be steady before reliable slant
range is available when AC depresses the bomb but¬
ton. Bombing accuracy is also affected by long slant
ranges and by high G acceleration during pull-up
after pickle. After T.O. 1F-4D-507, the computer
accuracy increases by adding a vertical velocity ac¬
celeration compensator. This influences the release
point computation in the vertical plane.

Range tracking of the ground return can be rejected
by depressing the action switch momentarily to Half-
Action. Lock-on can also be broken by a nose-up
maneuver where the range rate is increased beyond
the range tracking capability of the radar. In this
case, tracking continues on memory for 5 seconds.

If the ground return signal reappears within 5 sec¬
onds, normal tracking is automatically resumed if
the position of the ground return coincides with the
position of the range strobe. When lock-on is broken,
the ASE circle and the range strobe is removed from
the display and the acquisition symbol reappears.
Refer to T.O. 1F-4C-34-1-1A for the classified de¬
scription of the Air-to-Ground Mode.

DIVE LAYDOWN BOMBING MODE

The dive laydown bombing mode is illustrated in fig¬
ure 1-27. The dive laydown bombing mode is essen¬
tially the same as the dive toss bombing mode (dive-
level maneuver) with the following exceptions for the
dive laydown mode:

a. The dive laydown bombing mode is used primarily
for the delivery of high drag weapons (CBU-1, CBU-2,
Snakeye I, etc.) where bomb range is relatively in¬
sensitive to deviations from the preplanned release
parameters.

b. The bomb range is manually set in the Release
Range control on the WRCS panel; the Drag Coeffi¬
cient control is not used.

c. The AC must fly the preplanned released true
airspeed (or ground speed) and the preplanned re¬
lease height above target that will produce the bomb
range set in the Release Range control.

The dive laydown bombing mode is selected by plac¬
ing the delivery mode selector knob to DIVE LAY
and positioning the weapons selector knob to either
RKTS & DISP (for dispensers only) or BOMBS. The
only controls used on the WRCS panel are the release
range control and, if required, the release advance
control. The value placed on the release range con¬
trol is the horizontal bomb range for a given release
altitude above target AGL and release true airspeed
obtained from the bombing tables.

1-68

Change 1

T.O. 1F-4C-34-1-1

DIVE LAYDOWN BOMBING MODE

--utt

VISUALLY TRACK TARGET MOMENTARILY

OPTICAL SIGHT:

1. Drift Stabilized

2. Reticle depressed to the
radar boresight line.

AH/APQ-109 MODE:

1. A/G

2. Al Range
WRCS Manual Inputs:

1 . Release Range
2. Release Advance
INS Supplies:

1 ■ Groundspeed
2. Pitch Angle

DEPRESS AND
HOLD BOMB
RELEASE
BUTTON

GROUND TRACK THROUGH TARGET

LEVEL APPROACH
AT PREPLANNED ALTITUDE
AGL AND AIRSPEED

AUTOMATIC

BOMB

RELEASE

CBU PATTERN

1/2 PATTERN'

RELEASE RANGE

angle to the WRCS computer. These inputs are used
to compute the horizontal distance to the target. The
WRCS computer continues to monitor the horizontal
range to the target with respect to the initial range
established when the bomb button was depressed.
When the aircraft is at the release range from the
target set in the release range control, the WRCS
automatically supplies a release signal to the weap¬
ons release circuits.

After the bomb button is depressed, the AC may in¬
crease the dive angle to arrive at a preplanned ap¬
proach altitude AGL. The final approach to the tar¬
get is made at the preplanned airspeed and altitude
above target.

LAYDOWN BOMBING MODE

The laydown bombing mode (figure 1-28) is used for
delivery of high drag weapons where the bomb range
is relatively insensitive to variations in preplanned
release conditions. The maneuver consists of a low
level approach and delivery at a preplanned release
altitude AGL and at a preplanned airspeed. The AN/

APQ-109 radar is not employed by the laydown bomb¬
ing mode. The lead computing optical sight can be
used, or an IP can be used, to establish a known
aircraft-to-target distance. The lead computing
optical sight is operated in the A/G mode. With the
laydown bombing mode selected, the reticle image
will be pitch stabilized with reference to the hori¬
zontal plane of the inertial platform and drift stabi¬
lized along the ground track. The reticle depression
is controlled by the reticle depression knob.

During mission planning, a desirable sight depres¬
sion angle for the planned release altitude is chosen
from the sight depression chart; (do not add fuselage
angle of attack) the resulting range from the aircraft
to target is established and entered in the target
range control (placarded ALT RANGE) on the WRCS
panel. The horizontal bomb range for the selected
release altitude and airspeed is obtained from the
bombing table and entered in the release range con¬
trol on the WRCS panel. For the CBU delivery, or
a ripple release, one-half of the pattern length may
be added to the value placed in the range control,
thereby, placing the center of impact on-target.

1-69

L Ay DOWN BOMBING MOVE

OPTICAL SIGHT:

1 . Drift and Pitch Stabilized

2. Reticle depression controlled
by RETICLE DEPR knob.

INS Supplies:

1 . Groundspeed
WRCS Manual Inputs:

1 . Target Range

2. Release Range

3. Release Advance
AN/APQ-109 MODE:

1. Not Required.

An IP may be used to establish the
target range if the optical sight is

APPROACH AT PREPLANNED
ALTITUDE AGL AND
AIRSPEED—n

AUTOMATIC BOMB
RELEASE-\

DEPRESS AND
HOLD BOMB RELEASE
BUTTON--

RELEASE RANGE

TARGET RANGE

Figure 1-28

When a value is inserted on the target alt
range counter other than 000, do not select
the target finding or offset bombing mode un¬
less: the aircraft altitude MSL is greater than
the value (times 100) or, performing the tar¬
get find/offset bomb WRCS BIT check as pre¬
sented in section n. This is necessary to
prevent possible damage to the pitch servo
in the WRCS computer.

The approach to the target is made at the preplanned
altitude above target and preplanned true airspeed
(or a ground-speed that will produce the established
bomb range). When the pipper is on-target, the
bomb button is depressed and held until bomb re¬
lease. When the bomb button is depressed, the air¬
craft will be at the distance from target set in the
target range control, the INS begins to supply
ground-speed data to the weapons release computer,
and the ground-speed data is integrated with time by
the computer to establish the distance traveled from
the point. When the aircraft has traveled the dis¬
tance entered in the target range control minus the
value set in the release range control, a bomb re¬
lease signal is generated and routed to the release
circuit to initiate a bomb release.

1-70

The laydown bombing mode is selected by placing the ^
delivei'y mode selector knob to LAYDOWN and posi¬
tioning the weapons selector knob on RKTS & DISP or
BOMBS. On the WRCS panel, enter the preplanned
values in the target range control (the range light
under the ALT RANGE placard will illuminate when
LAYDOWN is selected) and the release range control.

The release advance control may also be used, if
necessary.

OFFSET BOMBING MODE

The offset bombing mode (figure 1-30) provides the
aircraft with an all weather (blind bombing), high and
low altitude, level bombing capability. The offset
bombing mode requires an IP to establish the position
of the aircraft with respect to the target. After the
aircraft position is supplied to the WRCS computer,
steering information is presented to the aircrew. The
navigation range from this point to bomb release can
be from 500 to 180, 000 feet. When the aircraft is at
the preset release range from the target, the bomb
is automatically released. To provide an IFR capa¬
bility, either the target or the IP must be radar de¬
finable. A radar definable IP is referred to as a
radar IP (RIP). To provide a VFR capability, a
prominent visual IP (VTP) must be used. The RIP
can be beyond the target or offset from the approach
course to the target — RIP-flyover is not required.

T.O. 1F-4C-34-1-1

OFFSET BOMBING MOVE and
TARGET FINDING MODE

THE TARGET IS EAST
OF THE RIP.

TARGET IS-._

NORTH OF 1
THE RIP T ,

TARGET

* AUTOMATIC
BOMB RELEASE
POINT

If the bomb button is depressed after the bomb release point (and held
depressed), the bomb will not be released until the aircraft has passed
the target.

* DEPRESS BOMB BUTTON
AND HOLD DEPRESSED
UNTIL RELEASE
If the bomb button is released,
it can be depressed again.

r ON
COURSE

TARGET

INSERT

OFFSET BOMBING MODE ONLY

DETECTION

Optical Sight:

1 . Gaged Zero 0 Azimuth.

2. Reticle Depressed to the
Radar Boresight Line.
AIS/APQ-109 Mode:

1. MAP-PPI.

2. AI Range .

WRCS Manual Inputs:

WRCS Panel.

1. Target N-fy^E-W Distance

2. IP Altitude MSL.

3. Release Advance.

4. Release Range.

Cursor Control Panel:

5. Freeze Signal.

6. Target Insert Signal.

7. Cross Track Signal.

8. Along Track Signal.

9. Reset Signa I.

INS Supplies:

1 . Ground Speed.

2. Altitude MSL.

3. Ground Track.

4. True Heading.

5. Aircraft Velocity East.

6. Aircraft Velocity North

Pilot Detects RIP
Return on Radar
Scope

Pilot Places Cursors
Over the RIP and
Depresses the Freeze
Button.

OFFSET

CURSOR

SIGHT

TARGET

Pilot Depresses Target
Insert Button. AC
Receives Range and
Steering Display and
Maneuvers to Target.

target

Maneuver Toward the
Indicator and Arrive on
Course to the Target.
NOTE: The Optical
Sight is not Drift Stabi¬
lized. PPI display
is Drift Stabilized.

(

{(.I)}

-■f.

F4D-34-1-218-1

Figure 1-29 (Sheet 1 of 4)

1-71

T.O. 1F-4C-34-1-1

WITH VISUAL IP

Optical Sight:

]. Reticle caged to the
Radar Boresight Line.

AN/APQ-109 Mode:

1. Not Required

WRCS Manual Inputs:

WRCS Panel

1. Target N-S/E-W Distance

2. Release Advance.

3. Release Range.

Cursor Control Panel

4. Freeze Signal.

5. Target Insert Signal.

6. Reset Signal.

INS Supplies:

1. Ground Speed.

2. Altitude MSL.

3. Ground Track.

4. True Heading.

5. Aircraft Velocity East.

6. Aircraft Velocity North.

TARGET

-W0E-

DEPRESS FREEZE
BUTTON AND THE
TARGET INSERT

* OFFSET BOMBING MODE ONLY

Depress the Freeze Button and
the Target Insert Button when
Aircraft is over IP. Steering
Information is Displayed.

HSI

BDHI

ADI

SIGHT

Maneuver Toward the Indicator
and Arrive on Course to the
Target. Note: The Optical
Sight is not Drift Stabilized.

- Note -

When over the target,
the roll tabs rotate and the
distance counters

begin increasing in value displayed.

F4D-34-I-218-2

Figure 1-29 (Sheet 2 of 4)

1-72

T.O. 1F-4C-34-1-1

D Bearing Pointer: Indicates the magnetic bearing
to the target as computed by the WRCS com¬
puter and controlled by the NS/EW target dis-
tance counter.

0 Heading Marker: Indicates the magnetic head¬
ing to the target as computed by the nav com¬
puter and controlled by NS/EW target distance
counter.

E Course Arrow: Indicates the magnetic course
of the aircraft (ground track), computed by the
nav computer; same as Course Window.

D Range Indicator: Indicates the horizontal dis¬
tance (not slant range) to the target in nautical
miles.

Q Course Window: Same as Course Arrow.

0 TGT Mode Light: Illuminates when the Target
Insert button is pushed on (if the instrument
lights are ON).

B Lubber Line: Indicates the magnetic heading of
the aircraft.

When the aircraft is on the magnetic
course to the target, the Bearing Pointer
and the Course Arrow are aligned, and the
Heading Marker is aligned with the top of
the Lubber Line.

D No. 1 Needle: Same as the Bearing Pointer
on HSI.

0 NA

0 No. 2 Needle: Same as the Course Arrow on
the HSI.

Q Range Indicator: Same as the Range Indicator
on the HSI.

S NA
0 NA

Q Top Index: Same as the top Lubber Line on
the HSI.

When the aircraft is on the magnetic
course to the target, the No. 1 Needle is
aligned with the No. 2 Needle.

F4D-34-I-218-3

Figure 1-29 (Sheet 3 of 4)

1-73

ADI STEERING

OFFSET BOMBING MODE: K*
DEPRESS AND HOLD BOMB ft*

ULI rU-JJ IIUUW

M BUTTON (SEE NOTE)

REDUCE BANK ANGLE TO
MAKE AN ASYMTOTIC APPROACH

Note

PRIOR TO BLOCK 28 WITHOUT INCORPORATION OF
T.O. 1 F-4-709 THE BANK STEERING BAR (VERTICAL
NEEDLE) WILL NOT SUPPLY STEERING INFORMATION
AFTER THE BOMB BUTTON IS DEPRESSED. FOR SUBSE
QUENT AIRCRAFT. THE ADI WILL PROVIDE STEERING
INFORMATION UNTIL ANOTHER DELIVERY MODE IS
SELECTED, OR THE RESET BUTTON IS PUSHED.

PROPER BANK ANGLE MAINTAINED

Figure 1-29 (Sheet 4 of 4)

T.O. 1F-4C-34-1-1

F4D-34-I-219.

IP SELECTION AREA F-4D

TO ESTABLISH THE TARGET COUNTER
SETTINGS; "THE TARGET IS LOCATED

_.FEET N OR S, AND-FEET E

OR W OF THE RIP."

RIP HI:

NORTH; 75,000 FT
EAST; 05,000 FT

RIP #2:

SOUTH; 10,000 FT
EAST; 50,000 FT

Note

MAXIMUM TARGET
DISTANCE SETTING
99,900 FT

99,900 FT

SELECTION

AREA

- 75,000 FT

50,000 FT

SOUTH

25,000 FT

- 25,000 FT

- 50,000 FT

TARGET

-75,000 FT

Figure 1-30

The AN/APQ-109 radar set is not used when a VIP
is used, and the aircraft must be flown directly over
the VIP to establish the aircraft position with respect
to the target - the approach can be made from any
direction. The final portion of the bombing run prior
to bomb release is performed at the preplanned re¬
lease speed and level approach altitude above target
AGL. The release altitude is normally between 50 to
1000 feet; however, the release altitude can be as
high as 50, 000 feet if the bomb range does not ex¬
ceed the release range control setting on the WRCS
panel (X10 or X100).

The offset bombing mode is selected by placing the
delivery mode selector knob to OFFSET BOMB and
positioning the weapon selector knob to either BOMBS
or RKTS & DISP (for dispensers only). The INS must
be in operation for all WRCS modes. The optical
sight is operated in the air-to-ground mode, and the
AN/APQ-109 radar is operated in the MAP-PPI

mode. The optical sight is electrically caged to 0° in
azimuth, and to the radar boresight line in elevation.
The roll tabs on the optical sight can be used to pro¬
vide steering information that will guide the AC to the
target; the ADI is the primary steering instrument.
The radar will be stabilized in drift, roll, and pitch.
The radar is used to identify the RIP and establish
the aircraft position with the aid of the cursor panel.

After target insert, the drift stabilized MAP-PPI
radar display can be used as the primary steering
instrument by flying to center the offset cursor on
its ZERO azimuth position. Also, after target in¬
sert, the radar should be switched to minimum scope
range to further increase bombing accuracy. Before
using the scope display as the primary steering in¬
strument, the aircrew must establish the ZERO
azimuth position of the offset cursor by performing
the WRCS BIT check.

1-75

T.O. 1F-4C-34-1-1

The WRCS computer receives manual inputs from the
WRCS control panel. The IP pressure altitude (or
IP altitude MSL) is placed in the readout control plac¬
arded ALT RANGE (the ALT light illuminates when
OFFSET BOMB or TGT FIND is selected). The re¬
lease advance control is set (if required), and the
release range of the bomb is set in release range
readout control. The position of the target with re¬
spect to the IP and the map coordinates is manually
inserted in the WRCS control panel. For example,
the target is located a number of feet north or south
of the IP, and the target is located a number of feet
east or west of the IP as measured on the target map
or photos. (Refer to figure 1-30,IP selection area.)
When the target presents an identifiable radar return
and is used as the RIP, the target range readout con¬
trols must be set equal to zero, and the target pres¬
sure altitude (or target elevation MSL) must be set
in the ALT RANGE readout control.

When a value is inserted on the target alt
range counter other than 000, do not select
the target find or offset bomb mode unless
(a) the aircraft altitude MSL is greater than
the value (times 100) or, (b) the aircrew is
performing the target find/offset bomb BIT
check as presented in section n. This is
necessary to prevent possible damage to the
pitch servo in the WRCS computer.

In situations where the known radar IP is actually
higher than the required approach altitude, the air¬
crew can avoid (through correct planning) any
equipment damage mentioned in the caution above.
Using the following method, the mission planner
determines a reciprocal altitude/range counter
setting with respect to the planned approach altitude.

a. Determine the approach altitude above MSL.

b. Determine the difference between approach alti¬
tude and the (higher) radar IP altitude (MSL).

c. Subtract the value of step (b) from the approach
altitude of step (a); place this amount on the ALT
RANGE counter. This establishes an IP altitude and
position which is as much below approach as the ac¬
tual IP altitude is above approach, and the radar
range to either point is the same.

d. During the mission, the AC must fly the planned
approach altitude during freeze and target insert
operations to assure that correct range data is avail¬
able for the computer.

The cursor control panel is used to supply computer
inputs which establish the position of the aircraft
with respect to the IP or RIP and initiate computer
operation. (These controls are discussed later.)

The INS supplies the following aircraft position in¬
puts to the computer:

a. Aircraft ground-speed.

b. The velocity vectors: north-south, east-west.

c. Aircraft altitude MSL (standard day).

d. Ground track.

e. Aircraft heading.

The computer uses these signals in conjunction with
the MAP-PPI radar and the inputs from the cursor
control panel to generate the following displays:

a. The position of the slant range cursor and the
offset cursor is displayed on both radar scopes.

b. Horizontal ground range to the target is displayed
on the HSI and BDHI instruments if the respective
mode selector switches are in NAV COMP.

c. Steering angle of the target is displayed on the
HSI, BDHI, ADI instruments, and the optical sight.

d. The bomb release signal is generated and routed
to the weapons release circuit to release the bomb.

OFFSET RADAR IP

When using a radar IP, the offset bombing run be¬
gins when the RIP is identified on the scope. The
pilot positions the range cursor below the RIP return
by moving the along-track control on the cursor con¬
trol panel. The cross-track cursor control is used
to position the offset cursor over the RIP radar re¬
turn. When the RIP return is at the intersection of
the cursors, the pilot may push the freeze button;
the cursors now begin tracking the RIP. After posi¬
tive tracking of the RIP is established and the air¬
craft is within 180,000 feet from the target, the pilot
may push the target insert button; the cursors auto¬
matically center over the target and begin tracking
the target. The cursor controls can be operated at
any time prior to Target Insert to update (touch-up)
the position over the RIP. If the target can be de¬
fined on the radar scope, the cursor controls can be
operated after Target Insert to update on the target,
providing, the RIP altitude is nearly the same as the
target altitude. When there is a difference between
the RIP and target altitude, the target pressure alti¬
tude (or target elevation MSL) should be placed in the
ALT RANGE readout control prior to updating on the
target.

If a visual flyover fix on the RIP is desired after the
cursors are tracking the target, the pilot must push
the reset button, and when the aircraft is directly
over the RIP, the freeze button and the target insert
button are depressed simultaneously. Steering in¬
formation will be presented to the AC on the ADI, the
HSI, and the optical sight. Steering information is
supplied to the pilot on the BDHI. The AC should use
the ADI as the primary instrument to maneuver the
aircraft on course to the target. Refer to figure 1-29.

Note

•Before T.O. 1F-4-709 in F-4D aircraft prior
to Block 28; the vertical needle on the ADI
cannot be used after the bomb button is de¬
pressed; the command heading marker and
bearing pointer may be used or optical sight
steering may be used. Ground track steering
is not available; therefore, with a crosswind
condition, the aircraft wiH fly an arcing flight
path to the target.

•ADI steering will not be available if the weap¬
on selector knob is on AGM-45.

1-76

Change 6

T.O. 1F-4C-34-1-1

craft at the required altitude AGL. The bomb button
must be depressed before the bomb release signal is
automatically supplied to obtain a bomb release. The
bomb button can be released and depressed again
(prior to bomb release) without aborting the offset
bombing run. The WRCS computer supplies the bomb
release signal when the distance to the target, minus
the bomb release range equals zero. Steering infor¬
mation to the target continues to be supplied. Another

Change 6

1-76A/(1-76B blank)

T.O. 1F-4C-34-1-1

bombing run on the same target can be made by flying
the steering instruments and depressing the bomb
button prior to the bomb release point; however, this
method increases the navigation range which will de¬
crease bombing accuracy.

WARNING

If the bomb button is depressed (and held de¬
pressed), after the bomb release range is
passed, the bomb will not be released until
the aircraft has traveled beyond the target a
distance equal to the preset bomb range.

VISUAL IP FLY-OVER

When an IP is chosen that will not provide a suitable
radar return, the aircrew must visually identify the
IP, and the aircraft must be flown directly over the
IP. The freeze button and the target insert button
are depressed simultaneously when the aircraft is
directly over the IP. The steering displays are then
available and the AC maneuvers the aircraft accord¬
ingly. If the MAP-PPI radar is in operation, the
cursors will center over, and begin tracking the tar¬
get. Prior to the IP, the reset button should be
pushed to ensure that the cursors are at zero-zero;
and, the along-track, cursor control must not be
moved prior to IP. The use of a visual IP will pro¬
duce greater bombing accuracy than for use of a
radar IP. This is due to the inherent radar ranging
tolerance error of the radar, and the position error
of cursors in establishing the exact location of the
RIP with respect to the aircraft. Bombing range
error can be further reduced by choosing an IP that
is located as near as possible to the bomb release
point, thereby, reducing the navigation distance.

TARGET FINDING MODE

The target finding mode (figure 1-29 sheet 1) is pro¬
vided to aid the aircrew in navigation from a radar
or visual IP to the target area. The operating proce¬
dures and steering displays are identical to the off¬
set bombing mode; the target-finding mode does not
supply a bomb release signal. When the aircraft is
over the target, the ADI vertical needle moves off to
the side and the roll tabs on the optical sight will
rotate, and the range indicator counter begins to in¬
crease in value displayed. (The range indicators
may not reach 000 MILES.)

The target finding mode is selected by placing the
delivery mode selector knob to TGT FIND and the
navigation computer switches in the NAV mode. The
AN/APQ-109 radar is operated in the MAP-PPI mode
and the optical sight in the A/G mode. The appli¬
cable switches of the ensuing bomb delivery mode
may be preset. The operating altitudes for this mode
are between 50 feet and 60,000 feet AGL. Steering
information is removed when another delivery mode
is selected or the reset button is pushed.

An alternate use of the target-finding mode is as an
aid to update the ASN-46 navigation computer set
from a radar IP having known coordinates. Set the
north/south and east/west target distance counters
for a real or imaginary target with reference to the
RIP. The target is the location where INS updating
will occur. Position the update switch to SET and
dial the latitude and longitude coordinates of the real
or imaginary target in the navigation computer con¬
trol panel. The pilot uses the cursor controls to es¬
tablish a computer fix on the RIP, depresses the
freeze button and the target insert button, and the AC
maneuvers toward the target. Place and hold the INS
update switch in the FIX position. When the BDHI
miles-to-go target counter reads zero and the bear¬
ing needle swings through 90° to the aircraft heading,
release the update switch to the normal position.

WRCS/LABS DELIVERY MODE

F-4D-32 and up; F-4D-24 thru 31 after T.O. IF-4-
702, the combined WRCS/LABS delivery modes are
available.

This modification to the weapon system enhances the
bomb delivery capability in both visual and non-visual
flying environments. The modification is accom¬
plished essentially for nuclear weapons deployment.
However, the equipment and delivery methods will
also apply in certain situations involving non-nuclear
weapons. Hence, the following discussion involves
no specific bomb, but simply assumes that some
bomb(s) — either high or low drag — is aboard
the aircraft.

The AC may select any one of six LABS bombing
modes (including DIRECT) on the delivery mode se¬
lector. The modified equipment will allow the air¬
crew to energize and use the WRCS target find func¬
tions in conjunction with any of these LABS modes,
and most specifically, the AN/AJB-7 modes (LADD,
LOFT, and O/S). In this case, the WRCS system is
being used to deliver an AN/AJB-7 activate signal at
the proper range from target and along any ground
track projected directly through the target. The fol¬
lowing is a general analysis of modifications that im¬
mediately affect aircrew operations.

a. The weapon delivery panel (figure 1-31) is on the
rear cockpit right console. The panel includes the
activate control switch, the target find switch, and
the range switch. These are lock-toggle switches
that detent laterally into position.

b. The WRCS system is programmed to provide an
extended release range scale to 100, 000 feet. This
pertains to the activate range in an ASQ-91/AJB-7
integrated mode, or the release range (Rr) in a
WRCS mode.

c. The WRCS release altitude operational limit is
extended to approximately 18, 000 feet in the dive toss
mode.

d. The addition of a gyro fast erect switch for the
AN/AJB-7 gyro system.

1-77

T.O. 1F-4C-34-1-1

| WEAPON DILI VERY PANilfcEffl

NORM ON Vr>v^RMHOlD / g l rs' NORMX 100 1

b lo

ACTIVATE TGT fIND RANGE '

' . V, . 4C-34-l-1-(34)'

Figure 1-31

OPERATION

In the following discussion, it is assumed that the
aircrew is familiar with AN/AJB-7 bombing methods
and the WRCS target find mode as they function when
individually selected. Also the aircrew must have
selected the weapon aboard and performed all pre¬
arming functions. Assume here that the aircrew in¬
tends to plan the LADD/Target find bombing mission
(figure 1-32).

The aircrew selects TIMED LADD, and energizes
the appropriate release and arming switches for the
type of weapon aboard. The flight director instru¬
ments are placed in the nav. comp, operating mode,
and the optical sight is operated in the A/G mode.

On the weapon delivery panel, the pilot must select
HOLD on the target find switch; the HOLD position
selects the WRCS target find mode of operation.

The WRCS computer control panel is set as it nor¬
mally would be for offset bomb operations. The only
difference is that the release range (Rr) counter
must be set with a number representing range from
pullup to burst, which is quoted in the appropriate
LADD ballistics table. Assume that the ballistics
table range (Rg) is quoted at 14,000 feet. This is the
range at which the WRCS system delivers a signal
activating the LADD system. The aircrew should
allow for a small amount of lead-in time at pullup.
The lead-in time compensates for any delay in pilot
reaction time, and allows time for the AN/AJB-7 to
activate into the LADD mode. A feasible lead-in in¬
terval is 1 second, which is placed on the pullup
timer (T^ interval, figure 1-32). Therefore, the Rr
setting on the WRCS control panel is

Hr = R b + V A (1.69) Tj.

where Rg is the bombing table range. V A is approach
velocity in knots, and Ti is the desired lead-in time.
For a 1.0 second Tj interval and 550 KTAS approach,
the Rr setting would be 14, 900 feet. In the Rr
counter, the pilot would place 149 on the dial and
energize the range switch to (X100) on the weapon
delivery panel. Finally, the pilot sets the T 2 inter¬
val on the release timer.

Note

•The selection of 1.0 second for a lead-in in¬
terval is only intended as an example here.
Whatever the setting is, it should be as small

as possible since chances of distance error
at the pullup point are increased with longer
Ti intervals. Also, the activate tone is trig¬
gered at the activate point, regardless of the
value placed on the pullup timer. Hence, the
tone may be used both as an activate signal
and a pullup warning signal only if the pullup
timer is set on a low value, Finally, if Tj
is set to zero, the 0.38 second activate tone
occurs directly at the pullup point.

• With the range switch on (X100), the (X10)
factor on the release range counter has no
meaning. The range switch is also functional
in any WRCS mode that requires an Rr set¬
ting.

• For the WRCS/LABS modes, any release ad¬
vance (Ra) setting on the WRCS panel ad¬
vances the activate point by the amount set
into the counter. Normally, the counter
should be set on zero. However, an Ra set¬
ting may be used to apply a tailwind correc¬
tion or to apply a reaction time correction
during the TGT FIND/DIRECT mode.

As figure 1-32 indicates, the AC approaches the tar¬
get area using normal target find (or offset bomb)
procedures. The aircrew may select the target as
the IP, use an offset IP, or a visual IP fly-over pro¬
cedure may be used depending on the nature of the
target and weather conditions. Once the target insert
function is performed, the pilot places the activate
switch to ON. Note that if the activate switch is
placed ON before target insert, the LADD system
could energize prematurely. (At target insert, the
WRCS range servos position out to the aircraft range
from target. If the servos pass through the Rr set¬
ting, the AN/AJB-7 system could activate at that
instant.)

When the aircraft reaches the AN/AJB-7 activation
range (14, 900 feet in this case), a signal from the
WRCS triggers the activate tone and starts the pullup
time (Ti). At this point, the ADI needles switch into
the AJB-7 mode, but the remaining steering devices
continue indicating target find steering. The activate
tone lasts about 1/3 second, which means that the AC
has about 2/3 second remaining to react and begin
pullup as the T 2 interval (release timer) begins.

Notice that the bomb button may be depressed any¬
time during the (Ti + T 2 ) interval; AN/AJB-7 activa¬
tion occurs automatically and independently of the
bomb button when reaching the set Rr range. How¬
ever, if the pickle signal is delivered before reach¬
ing the activation range, the AN/AJB-7 sequence will
begin immediately. Also, if the AC inadventently re¬
leases the bomb button during (Ti + T 2 ) interval, the
signal may be reapplied before T 2 run-out without
aborting the run. The lock-out relays are bypassed
in the WRCS/AJB-7 modes.

1-78

Change 6

WRCS/LADD VEUVERy MOVE / F-4D j

RELEASE

PULLUP

POSITION

UPDATE

AJB-7

ACTIVATE

llll

l 1

i « ■

// 1

1 1

.1.

inp:

O POSITION UPDATE

PULLUP

1 . Pilot positions WRCS cursors over IP and de¬
presses FRZ control.

2. Pilot depresses TGT INS control, steering
displayed on HSl, ADI, reticle, and BDHI. AC

steers to null azimuth indicators.

3. Pilot selects ACTIVATE sflfir cursors and steer¬
ing devices complete transition to target.

O AJB -7 ACTIVATION (R R)

1 • Activate tone sounds (0.38 sec. beep) and Tj
time starts. (Tj =1.0 sec. lead-in time.)

2 . ADI pointers centered .

3. Pullup light on,

4. AC starts pullup.

• Bomb button signal may be delivered anytime
during Ti +T 2 .

•All other steering instruments (except ADI)
continue WRCS steering.

1. ATT] = 0, pullup light off.

2. Reticle light off.

3. Steady tone on.

4. T 2 time starts.

5. ADI pointers:

Horizontal - LADD vertical flight path.

Vertical - yaw/roll error.

6. Bomb button signal must be delivered before T 2 = 0.
O RELEASE

1. AT T2 = 0, release occurs.

2. Pullup and reticle light on.

3. Tone off.

4. ADI vertical pointer out of view.

0 RELEASE BOMB BUTTON

1. Pullup light off.

2. ADI vertical pointer-WRCS steering.

3. ADI Horizontal pointer out of view

4. WRCS steering continues, aircrew may re-attack
from another direction.

F4D-34-I-221

Figure 1-32

1-79

T.O. 1F-4C-34-1-1

Note

The 1/3-second activate tone mentioned here
is available only in the WRCS/LABS delivery
modes. If the AGM-45 is to be delivered us¬
ing the WRCS/LOFT mode, the pullup acti¬
vate tone is not available.

The pullup-to-release portion of the LADD maneuver,
with which the aircrew is familiar, is flown as figure
1-32 indicates. Aircrews may easily equate the pro¬
cedures shown in the figure 1-32 to any other LABS
maneuver. With a LOFT or O/S mode selected for
example, release occurs through the AN/AJB-7 gyro
rather than the release timer. The Rr counter is set
as a function of the desired pullup distance from tar¬
get, which would be nearly zero in an O/S mode and
conceivably as much as 30,000 feet in a LOFT mode.
Also, with the Rr counter set for a known bomb
range, the AC can select DIRECT and apply the re¬
lease signal when the activate tone sounds. In this
case, the aircrew has a DIRECT/TGT FIND release
mode. After bomb release, the WRCS target find
mode continues to function and the AC may reattack,
provided that the navigation range of the WRCS is not
exceeded (30 nautical miles). If the AC desires, the
system is completely recycled by placing the activate
switch to NORM and by depressing the reset button
on the cursor control panel. The AN/AJB-7 system
recycles automatically at bomb release.

WEAPON DELIVERY PANEL

TGT Find Switch

The selective functions of the target find switch and
the TGT FIND mode on the delivery selector are
identical. If the AC selects a WRCS mode on the de¬
livery selector, the target find switch has no function
and should remain in NORM. The HOLD position en¬

ergizes the target find circuits along with any LABS
mode (including OFF) that the AC selects.

Range Switch

The range switch is functional in any WRCS mode
that requires an Rr setting. The (X100) position ap¬
plies a multiplier of 100 to whatever digit the pilot
places in the Rr counter. In NORM, a factor of 10
is applied to the Rr setting.

Activate Switch

Voltage is available for the activate switch when the
target insert button is depressed. Placing the acti¬
vate switch to ON provides continuity to activate cir¬
cuits in the weapon release computer. These circuits
close only when the aircraft range from target be¬
comes equivalent to the set Rr range. This applies
the activate signal to the selected LABS circuits and
the associated indicators. To avoid premature acti¬
vation, select the ON position only after target in¬
sert, and only after the range and steering devices
have transitioned to the target. If the activate switch
is left in NORM, the system is operating in a target
find mode where an Rr setting has no meaning.

AUX ARMAMENT CONTROL PANEL

Gyro Switch

The AC may fast-erect the AN/AJB-7 gyro platform
by selecting the momentary FAST ERECT position on
the gyro switch. This applies an electrical cage sig¬
nal to the gyro caging mechanisms. As the caging
signal is applied, the aircraft should be in level, non¬
accelerating flight. The switch would have applica¬
tion, for example, to correct any noticeable gyro
precession during the level, constant speed target
run-in.

JETTISON CONTROLS (F-4D)

EMERGENCY JETTISON

Illustrations that demonstrate the jettison methods
and controls are provided in section IH. The inboard
and outboard MAU-12 armament pylons cannot be
jettisoned. The applicable jettison controls will jet¬
tison the MER's, TER's, or weapon suspended from
the armament pylons. The LAU-34/A launcher can¬
not be jettisoned; the jettison controls will jettison
the AGM-12B or AGM-45 from the launcher without
motor ignition. The LAU-7A/A and AIM-4D launch¬
ers are bolted to the inboard armament pylon and
cannot be jettisoned; the applicable jettison controls
launch the missiles with motor ignition. When the
inflight lockout pins are installed, the LO, RI and LI

unlocked lights on the DCU-94/A control-monitor
illuminate. The RO UNLOCKED light does not illu¬
minate when the lockout pin is installed.

EXTERNAL STORES EMERGENCY RELEASE BUTTON

The external stores emergency release button, plac¬
arded EXT STORES EMER REL, is a momentary
contact, pushbutton switch used to jettison all sta¬
tions simultaneously. This control is referred to as
the panic button. The button is in the front cockpit
on the left vertical panel. Jettison procedures and
the conditions are contained in section m.

1-80

Change 2

T.O. 1F-4C-34-1-1

SELECTIVE JETTISON

CENTERLINE STATION JETTISON

The centerline station jettison switch (figure 1-33)
is a cover-guarded switch on the left console fuel
control panel. The switch has two positions: NORM
and JETT. The switch is spring-loaded to NORM.
Placing the switch to JETT supplies jettison voltage
to the centerline station. Refer to section III,
Jettison procedures.

INBOARD WING STATION (MISSILE JETTISON
SELECTOR)

The missile jettison selector knob is a rotary type
pushbutton switch on the missile status panel. This
switch provides selective jettison of the fuselage
missiles and inboard wing stations. The switch po¬
sitions are as follows: OFF, R FWD, R WING,

R AFT, ALL, L AFT, L WING, and L FWD. Jetti¬
son voltage is supplied to the left or right inboard
stations by selecting L WING or R WING, and push¬
ing the jettison button. Refer to section III, Jettison
Procedures.

OUTBOARD WING STATION JETTISON

The wing station jettison switch placarded WING STA
JETT, is a cover-guarded, momentary contact
switch, spring-loaded to NORM. The switch is on
the fuel control panel. The switch has two positions:
NORM and JETT. Placing the switch to JETT sup¬
plies jettison voltage to the left and right outboard
wing stations. Refer to section III, Jettison Proce¬
dures.

Outboard Station Selective Jettison (After T.O. 1F-
4-863)

The outboard pylon jettison select switch (figure
1-33) provides a selective jettison function for the
outboard wing stations. The switch is positioned to
either LEFT, RIGHT, or BOTH, and then the wing
station jettison switch is energized to jettison the
contents of the outboard station(s). This is actually
a five-position switch with two positions not plac¬
arded. The center (straight up) position is OFF; the
inboard position is not in use and is essentially
another OFF position. Selecting either of these
(OFF) positions disables the wing station jettison
switch. The selective LEFT and RIGHT positions
enable the AC to meet specific jettison limitation re¬
quirements if an unsymmetrical external store load
exists on the outboard stations.

ARMAMENT SAFETY OVERRIDE PANEL

The armament safety override button is a push type
switch consisting of a holding coil and three individ¬
ual double pole switches ganged together by a common
plunger shaft and is spring-loaded to OFF. The con¬
trol is above the left console in the front cockpit.
When the override button is depressed, 28v dc is
directed to the holding coil from the R 28v dc bus.

This holding coil keeps the override button de¬
pressed, and directs power from the essential 2 8v dc bus
to emergency jettison circuits and from the R 28v dc
bus to the armament bus relay. The jettison circuits
are placed in an inflight configuration.

With the armament override button depressed,
a hazard exists if a centerline station fuel
tank is jettisoned on the take-off roll.

LANDING GEAR CONTROL HANDLE

The landing gear control safety switch is integral
with the landing gear control handle and is used to
prevent the inadvertent application of electrical
power to the armament circuits. When the gear han¬
dle is UP, this switch directs electrical power from
the R 28v dc bus to the No. 1 miscellaneous relay
panel, closing the armament bus relay. The arma¬
ment bus relay then supplies electrical power to the
armament circuits. When the gear handle is DOWN
power is applied through the safety switch to the
armament safety override button holding coil; thus,
the armament safety override button remains pulled
in when depressed.

LEFT MAIN GEAR SCISSOR SWITCH

The left main gear scissor switch is mounted on the
left main gear strut; it is actuated by a cam on the
bottom of the gear scissor hinge. When the strut ex¬
tends, the scissor links spread and the cam rotates
against the scissor switch, depressing the plunger.
The scissor switch makes contact when the plunger is
depressed. This switch, when closed, will allow
electrical power to go from essential 28v dc bus to
the external stores jettison switch, centerline tank
jettison switch, and the nuclear weapons jettison
switch. The armament safety override button by¬
passes the gear scissor switch and supplies elec¬
trical power to the jettison and release circuits for
ground operation.

NUCLEAR STORES RELEASE AND JETTISON

Most equipment suspended from both inboard arma¬
ment pylons, the left armament pylon and the Aero
27A centerline bomb rack can be jettisoned through
the nuclear store release circuit DIRECT release
mode. This is accomplished through the DCU-94/A
control monitor and the bomb button. Refer to sec¬
tion III for procedures. The nuclear release circuit
(DIRECT mode) will not jettison the left outboard
MER when the MER is shifted aft. The nuclear jetti¬
son circuit (NUCLEAR PUSH TO JETT) will jettison
a left/aft shifted outboard MER. However, the right
outboard station could also jettison even though only
the left outboard station is selected on the DCU-
94/A.

Change 8

1-81

T.O. 1F-4C-34-1-1

InF-4D aircraft with T.O. 1F-4-801, the
nuclear store release and jettison circuit
should not be used for selective jettison
from a particular station. The nuclear store
jettison button (NUCLEAR PUSH TO JETT)
should be used as a last resort, and only
when the inadvertent jettison from unselected
stations is of little concern. For example;
the fuselage missiles may jettison, and both

■ inboard stations and CL station may jettison
even though only the right or left inboard
station is selected on the DCU-94/A. Both

■ outboard stations and CL station may jettison
even though only the left outboard station is
selected on the DCU-94/A. When the center-
line station is selected, only the centerline
station is expected to jettison.

ECM POD JETTISON (STATION 9)

On aircraft F-4D-24 thru F-4D-30 an ECM pod on
station 9 is jettisoned by placing the wing station
jettison switch to JETT. However, this jettisons the
contents of both wing stations. On aircraft F-4D-31
and up, an ECM jettison switch (figure 1-33) provides
station 9 ECM pod jettison capability. The two-posi¬
tion cover guarded switch is placarded JETT and
NORM. The ECM pod may be jettisoned indepen¬
dently from station 9 (other armament retained) by
placing the switch in the JETT position. Also, the
wing station jettison switch may be used to jettison
stores from the left outboard station without releasing
the ECM pod. When armament is carried on stations
1 and 9, the ECM jettison switch is bypassed and the
wing station jettison switch jettisons armament from
both outboard stations. Inadvertent pod release during
ground operation is inhibited by the protective circuits
discussed earlier in this text. After T.O. 1F-4-863,
the outboard station selective jettison switch may be
used to individually jettison the outboard station load.

ECM

JETTISON

CENTERLINE
STA JETT SWITCH

4C—34— 1— 1—< 36)

Figure 1-33

Note

ECM pods (except pods on stations 4 and 6)
are also jettisoned by depressing the exter¬
nal stores emergency release button. How¬
ever, any decision to jettison ECM pods must
be left to the proper command authority.

MULTI-STATION ECM POD JETTISON

MISSILE JETTISON

After T.O. 1F-4-821, ECM pod provisions are added
to stations 2 and 8. Also after T.O. 1F-4D-547,
multi-station ECM capabilities include stations 2, 4,
5, 6 and 8. ECM pods on stations 2, 5, and 8 are
jettisoned by following the normal jettison procedures
for those stations. Jettison controls are illustrated
on figure 1-33. ECM pods on stations 4 and 6 cannot
be jettisoned.

The jettison circuitry within the firing circuits is
controlled by the missile jettison knob on the missile
status panel. The AC may manually select only one
of the fuselage missiles, or either of the inboard
wing stations for jettison. Before the missiles
can be jettisoned, the emergency landing gear
handle must be IN and the weight must be off
the landing gear or the landing gear handle must

1-82

Change 7

T.O. 1F-4C-34-1-1

be UP. For ground checkout purposes, these inter¬
locks can be bypassed with the armament safety
override button.

Radar Missile Jettison

When the missile jettison knob is pushed to jettison
the fuselage stations, the ejection squibs are acti¬
vated any time power is on the aircraft. The ejectors
used to launch the fuselage missiles are activated by
jettison voltage and not the fire voltage. These
ejectors are gas cartridges which explode to eject
the missile downward from the fuselage. The jettison
circuitry for the two forward fuselage missiles is
interlocked in such a manner that, if the TK light
is illuminated, the missiles cannot be jettisoned.

The AIM-7D/E missiles are jettisoned without motor
ignition.

Note

After T.O. 1F-4-750, the TK light is on be¬
fore and after the M118 or MK 84 bomb is
released when the centerline single bomb
shorting plug is installed. Even though the
TK light is on, the tank aboard relay is not
energized, permitting the two forward
AIM-7 missiles to be monitored, launched,
and jettisoned.

Heat Missile Jettison

The jettison knob on the missile status panel allows
the pilot to jettison the AIM-4D and AIM-9 missiles.
The AIM-4D jettison sequence is not the same as
the firing sequence. For left wing: L BOTTOM,
after 0.2 sec., L INBOARD. For right wing: R IN¬
BOARD, after 0.2 sec., R BOTTOM. For ALL:

L BOTTOM and R INBOARD, after 0.2 sec., L IN¬
BOARD and R BOTTOM. When the missiles are
jettisoned, the rocket motors are ignited and the
missiles are fired ballistically (no guidance, no
self destruct). The normal preparation of the mis¬
siles is not accomplished; therefore, the warhead
fuze in the missile is not armed at launch. There
is a 0.2-second delay between two AIM-4D missiles
launched on the same station. The flaps must be UP
to jettison theAIM-4D or AIM-9 missiles. TheAIM-
4D and AIM-9 launch and jettison circuit is inter¬
locked with trailing edge flaps circuit to prevent in¬
terference during launch. The speed brakes may
sustain damage if they are extended during missile
launch or jettison. The landing gear must be up to
jettison the AIM-4D missile. For AIM-9 jettison,
the weight must be off the left main landing gear,
i.e., the AIM-9 can be jettisoned if the gear is down
and the aircraft is in flight. For AIM-4D missiles,
the gear up relay is located in the AIM-4D launcher
and prevents AIM-4D launch and jettison until the
gear is up (left main gear door closed).

SUSPENSION EQUIPMENT (F-4D) I

BRU-5/A BOMB RACK
(AERO-27/A)

The BRU-5/A bomb rack (figure 1-34 sheet 3) is a
self-contained ejector unit mounted within the air¬
craft at centerline station 5. The Aero-27/A rack
has four suspension hooks: two 14 inches apart and two
30 inches apart. The BRU-5/A rack has only 30-inch
hooks, and arming solenoids in place of the 14-inch
hooks. An ejector piston is located in the center of
the rack. Operation of the rack hooks and the ejector
piston is initiated through the jettison circuit or the
nuclear release circuit by igniting two ejector car¬
tridges. Gases from the ejector cartridges cause the
rack hooks to open and the ejector piston to push
downward on the bomb or suspension equipment. With
the bomb rack safety pin installed, an electrical
safe switch is opened to prevent the cartridges from
firing; the pin is removed prior to flight. The
MER cannot be suspended from the bomb rack with¬
out the centerline bomb rack adapter. The weight
of the Aero 27/A bomb rack (51 pounds) is not in¬
cluded in the basic weight of the aircraft and must be
included in any gross weight computation. The weight
of the BRU-5/A is 45 pounds.

After T.O. 1F-4-750, the two 14-inch suspension
hooks are replaced by two arming solenoids. A

centerline single bomb shorting plug is installed to
permit the release of the MK 84 or M118 GP bomb
through the conventional release circuit. Illumina¬
tion of the TK light reveals the installation of the
shorting plug.

Note

Even though the TK light is on, the tank
aboard relay is not energized; therefore, the
forward AIM-7 missiles can be monitored,
launched, and jettisoned.

After the bomb is released, the amber station select
light remains on and the TK light also remains on.
The Ml 18 or MK84 on centerline can be jettisoned
with the external stores jettison button, the center-
line tank jettison switch, the nuclear store jettison
button, and can be released through the DCU-94/A
control monitor.

CENTERLINE BOMB RACK ADAPTER

The centerline bomb rack adapter is attached to the
centerline position to accept the MER assembly. The
adapter is compatible only at the centerline, and
attaches directly to the BRU-5/A bomb rack. The
adapter weighs 55 pounds.

Change 6

1-83

T.O. 1F-4C-34-1-1

MAU-12B/A, C/A ARMAMENT PYLONS

The inboard and outboard armament pylons (figure
1-34, sheets 1 and 2) are bolted to the wing at sta¬
tions 1, 2, 8, and 9. The pylons cannot be jet¬
tisoned. Each armament pylon assembly includes
the MAU-12B/A ejector rack, weapons relay panels,
a power rectifier, and bomb release circuits. The
ejector rack contains two cartridge breeches and
ejector pistons, 14 and 30-inch suspension hooks,
three arming wire solenoids, and a solenoid oper¬
ated assembly that electrically locks (safeties) the
cartridge fire circuit. When the cartridges detonate,
gas pressure opens the rack hooks and forces the
pistons downward, ejecting the bomb. To compen¬
sate for various bomb CG locations, orifices are in¬
stalled into the rack to control bomb separation char¬
acteristics by varying the forces delivered to each
piston. The ground safety pin when installed pro¬
vides only a mechanical lock in the hook linkage for
ground safety purposes. The inflight safety lockout
solenoid electrically isolates the cartridges by me¬
chanically controlling two switches that break the
cartridge circuit. The lock must be removed when
the MER or TER is aboard by manually installing
the inflight safety lockout pin (or bolt) in the pylon.
The bolt is installed only for non-nuclear bomb
carriage and must be removed for nuclear carriage.
When the bolt is installed, the DCU-94/A UNLOCK
light for that station illuminates continuously (ex¬
cept the RO UNLOCK light). The arming wire sole¬
noids are controlled by the position of the arm nose
tail switch.

Note

The MAU-12C/A is completely interchange¬
able with the MAU-12B/A armament bomb
rack. The MAU-12C/A is a strengthened
MAU-12B/A.

MULTIPLE EJECTOR RACK (MER)

The multiple ejector racks, used at the outboard
wing stations and the centerline station are: MER-
10 and -10A. The MER-10A functions differ from
the MER-10 as follows:

a. Only the loaded MER-10A stations receive a re¬
lease pulse regardless of the arm nose tail switch
position.

b. The MER-10A is automatically homed to the first
loaded station in sequence each time power (28v dc
Ess Bus) is applied to the aircraft. The MER-10A
does not have a homing light.

c. The step switch on the MER-1QA is used for
ground checkout operation.

identified with a number corresponding to its release
sequence. All MER's are rigged 1° nose down for
rockets. The centerline MER weight is 215 pounds,
the outboard MER weighs 225 pounds.

TRIPLE EJECTOR RACK (TER)

The triple ejector racks used at the inboard wing
stations are TER-9 and TER-9A. The TER-9A func¬
tion differs from the TER-9 as follows:

a. The TER-9A is automatically homed to the first
loaded station in sequence each time power (28v dc
Ess Bus) is applied to the aircraft. The TER-9A
does not have a homing light.

b. The step switch on the TER-9A is used for
ground checkout operation.

c. Only the loaded TER-9A stations receive a re¬
lease pulse regardless of the arm nose tail switch
position.

The TER has two suspension lugs mounted 30 inches
apart. It consists of three 14-inch ejector units, six
arming solenoids, control unit and wire bundles re¬
quired to arm, release, and/or fire munitions that
are carried. Each ejector rack or point is identified
with a number corresponding to its release sequence.
TER's are permanently rigged 1° nose down. The
TER weighs 95 pounds.

LAU-34/A LAUNCHER

This assembly must be used to carry and launch the
AGM-12B and AGM-45A missiles. The launcher
contains the electrical circuits and relays which are
responsible for the dispersal of missile pre-heat,
pre-arm, and missile launch voltage, The method of
carriage is illustrated (figure 1-34 sheet 1). The
launcher also contains a cartridge-fired jettison gun
assembly. Expanding gas from the detonated car¬
tridges operates the assembly and slides the missile
rearward free of the launcher rails. The missile
freefalls in an inert state.

REHOMING MERS AND TERS

A hung bomb can be released, in some cases, after
rehoming the MERs and TERs. Rehoming is accom¬
plished in flight by cycling the weapon selector knob
from BOMBS to RKTS & DISP and back to BOMBS.
This action causes the station stepper switch in all
MER/TERs aboard to move from the OFF position
to the first loaded station in sequence. The stepper
switch will not move if on a loaded station or the
MER/TER is empty. (A defective store aboard sens¬
ing switch could cause the MER/TER to appear
empty.) The MER/TER stepper switch OFF position
is obtained only in the BOMBS mode and after a re¬
lease pulse has been sent to each of the loaded sta¬
tions on the MER or TER. Additional bomb release
pulses will not move the stepper switch from the
OFF position. Selecting RKTS & DISP moves the
stepper switch from the OFF position because there
is no OFF position in the MER/TER with the RKTS
& DISP mode. The MER/TER stepper switch always
steps to the next loaded station and continues to re¬
peat the cycle when the RKTS & DISP mode is used.

1-84

Change 5

T.O. 1F-4C-34-1-1

SUSPENSION EQUIPMENT j F-4D / HK

- -

MAU-12 BOMB RACK
SAFETY PIN

64C13362 (AF)

ONE REQUIRED IN EACH
ARMAMENT PYLON

CERTAIN STORES ARE ALSO
LOADED DIRECTLY ONTO MAU-12
BOMB RACK.

v SAFETY PIN
4815973-1 (DOUGLAS)

TWO SAFETY PINS REQUIRED
FOR EACH MER/TER
EJECTOR RACK.

HOMING SAFETY
EIGHT PIN

HOMING

ROCKET

SAFETY PIN (ELECTRICAL)
4815967-1 (DOUGLAS)
F^one safety pin required

^ IN EACH MER/TER RACK.

1. LAU-34/A MISSILE LAUNCHER
(AGM-12/B & AGM-45 MISSILES)

2. EJECTOR RACK PISTON (2)

3. MAU-12 EJECTOR RACK

4. INFLIGHT SAFETY LOCKOUT PIN (BOLT)

5. (o) TRIPLE EJECTOR RACK ASSY (TER)

(b) MULTIPLE EJECTOR RACK ASSY (MER)

6. EJECTOR RACK, MER/TER

7. AGM-12 LAUNCHER BUNDLE (FWD)
AGM-45 LAUNCHER BUNDLE (AFT)

8- JETTISON GUN ACCESS

9. AFT. MISSILE RETAINER

10. FWD MISSILE RETAINER

11. MISSILE/LAUNCHER CONNECTOR

Figure 1-34 (Sheet 1 of 4)

Change 2

1-85

T.O. 1F-4C-34-1-1

OUTBOARD ARMAMENT PYLON

F-4D

: auIOn

HOOK MANUAk
•tit AH

CAUTION t

i> RIO 1HMI

Vrtl«U I'Nt'AO*

n UNVAHHEO

GROUND SAMI'

AtMMG
SOI fWOJP

WITHOUT CARTRIDGES

MOO* MANUAI
H If AH

CAUTION

l> RID VIA'I
VlStW.1 UNKAC1
1% UMk.AlCMtO

GROUND lAff!V
>*|N HOU

ARMIJO

JO'fNOfD

WITH CARTRIDGES

MAU-12 BOMB RACK
SAFETY PIN 64C13362-3 (AF)

ff> ONE REQUIRED IN EACH ARMA
MENT PYLON

F4D-34-1-223-2

Figure 1-34 (Sheet 2 of 4)

T.O. 1F-4C-34-1-1

CENTERLINE RACK

ROTATED 180°

* SAFETY PIN
48X5973-1 (DOUGLAS)

► TWO SAFETY PINS REQUIRED
FOR EACH MER/TER
EJECTOR RACK.

CENTER LINE RACK SAFETY PIN
MDE3254-301

» ONE SAFETY PIN REQUIRED IN THE
BRU-5/A BOMB RACK

1. CENTERLINE EJECTOR RACK (BRU-5/A)

2. ARMING SOLENOIDS (1 AFT 2 FWD)

3. CENTERLINE BOMB RACK ADAPTER

4. MULTIPLE EJECTOR RACK ASSEMBLY (MER)

F4D-34-I-223-3

Figure 1-34 (Sheet 3 of 4)

-8'

SUSPENSION EQUIPMENT I F-4D

(CONTINUED)

NORMAL FORWARD SUSPENSION

OUTBOARD

MER SHIFTED AFT

For some weapons, the
MER must be shifted AFT
to observe Aircraft
C.G. requirement.

CENTERLINE

NORMAL FORWARD SUSPENSION

MER SHIFTED AFT

Figure 1-34 (Sheet 4 of 4)

provided the MER/TER stepper switch has arrived
at the OFF position.

a. Improper homing of the MER's or TER's.

b. Moisture in the bomb ejector rack breech that
grounds -out the release signal. After the MER's
and TER's are rehomed, succeeding release pulses
can (in some cases) generate sufficient heat to
evaporate the moisture in the bomb ejector rack
breech.

The following causes for failure of the bomb release
circuit cannot be corrected inflight by rehoming the
MER’s and TER’s:

a. Faulty ejector rack cartridges .

b. Broken or shorted wiring to the ejector rack
cartridges .

c. Faulty relays.

Note

• Do not confuse the rehoming procedure per¬
formed by the aircrew with the homing pro¬
cedure performed by the load crew. The load
crew will position the STEP-OFF-HOMING
switch on the MER or TER to HOME and ob¬
tain a steady green light. After the load crew
has homed the MERs andTERs, theRKTS&

DISP position will not move the stepper switch.

• The TER-9A and MER-10A is automatically
homed to the first loaded station in sequence
each time power (28v dc Ess Bus) is applied
to the aircraft. The load crew does not home
the MER-10A nor TER-9A.

The following causes of bomb release failure can be
corrected in flight by rehoming the MER'sand TER's

1-88 Change 5

T.O. 1F-4C-34-1-1

If all the bombs carried do not release, the ejector
racks should be rehomed and release attempted
again. Rehome the MERS and TERS as follows:

| a. Weapons selector knob - RKTS & DISP

The weapon selector knob is the only switch neces¬
sary to rehome all the MER's and TER's to position
the release pulse at the next loaded point of all sta¬
tions regardless of the station selected. After the
remaining switches are set for bomb release, the
bomb button is depressed and held for 4 seconds with
BOMBS/RIPPLE selected. With the MER-10/TER-9,
if the weapon does not release when the arm nose tail
switch is in an armed position, rehome and then re¬
peat the BOMBS/RIPPLE release procedure with the
arm nose tail switch in SAFE. If the station loaded
sensor switch has failed in the station empty position,
releasing the weapons safe supplies a release pulse
to the loaded stations and the unloaded station.

Note

• The arm nose tail switch position does not
affect the operation of the TER-9A, MER-
10A stepper switch; the release pulse is
directed only to the loaded stations.

• If the bombs cannot be released after per¬
forming the preceding procedures, it must
be assumed that the ejector rack cartridges
will not fire, or that the MER or TER is
malfunctioning.

Consider the situation where three rocket launchers
are loaded on a TER. The TER stepper switch is on
position No. 1. The TER stepper switch has four
positions: 1, 2, 3 and OFF. The first loaded point
in sequence is referred to as the home position.
Assume that the rocket launchers on points one and
two have been fired-out and the rocket launcher on
point three is full, i.e., no attempt was made to fire
the remaining rocket launcher. (The full launcher
must be released or fired before the empty launchers
can be released.) To release the rocket launchers,
the weapon selector knob is positioned to BOMBS.
When the bomb button is depressed, a pulse is sup¬
plied to release the full rocket launcher on point
No. 3. When the bomb button is released, or the
firing pulse is ended, the stepper switch moves to
OFF. Succeeding pulses will not move stepper switch
from OFF. To release the two i-emaining empty
launchers, the weapons selector knob must be posi¬
tioned to RKTS & DISP. Power is now supplied to the
stepper switch to position it to a loaded point; in this
case point No. 1. The AC can now select BOMBS and
release the two empty dispensers.

I CAUTION

Rocket pods and CBU dispensers (full and
empty) should be released from the MER/

TER in the normal bomb release sequence
to avoid possible aircraft damage.

There is presently no cockpit indication or procedure
to ensure which MER/TER station is selected for
BOMBS release after RKTS & DISP has been used.
The position of the MER/TER stepper switch is es¬
tablished by the number of dispensing signals to the
aircraft station and the number of dispensers (or
rocket pods) on that station; i.e., the number of dis¬
pensing pickle signals to a loaded station must be
equal to the number of dispensers loaded on that sta¬
tion (or a multiple of the number of dispensers on
that station) prior to selecting BOMBS to release the
dispensers/rocket pods from the MER/TER.

The release sequence is more likely to be out of se¬
quence when the outboard, inboard, and centerline
aircraft stations are not loaded with the same num¬
ber of dispensers (or rocket pods) and all aircraft
stations are selected for dispensing (RKTS & DISP/
SINGLE). For example: assume a configuration of
4 dispensers on each outboard station and dis¬
pensers on each inboard station and on the centerline
station (17 dispensers total). The inboai’dand center-
line stations should be deactivated after the third dis¬
pensing pickle (15 dispensers have been emptied).
After the fourth dispensing pickle to the outboard
stations, select BOMBS/RIPPLE, and hold the bomb
button depressed to release the dispensex’s from the
MER/TER in the normal bomb release sequence.

AERO-7A MISSILE LAUNCHER

Four Aero 7A launchers are mounted in the fuselage
so that four AIM-7 missiles are semi-submerged.
The Aero 7A launcher (figure 1-35, sheet 1) has two
ejector p.istons which are operated by gas generating
cartridges to eject the missile downward an approxi¬
mate 8 inches before the missile motor is fired.

E ach of the forward fuselage stations has a cavity
door that closes after the missile is gone, to smooth
the contour of the fuselage. Each launcher is elec¬
trically and mechanically protected from inadvertent
firing of the ejector cartridges by a safety pin which
is removed prior to flight.

Change 8

1-89

T.O. 1F-4C-34-1-1

AER0-7A LAUNCHER
SAFETY PIN (4)

AFT EJECTOR FOOT
MOTOR FIRE CONNECTOR

AERO-7A MISSILE LAUNCHER

ROTATED 180°

FORWARD MISSILE
HOOK

UMBILICAL CONNECTOR

WEIGHT INCLUDED IN BASIC WEIGHT
OF AIRCRAFT

FORWARD EJECTOR FOOT

MISSILE GONE SWITCH

AERO-7A MISSILE LAUNCHER

AIM-7 MISSILES

Figure 1-35. (Sheet 1 of 2)

AIM-4D MISSILE LAUNCHERS

(After T.O. 1F-4D-508)

An AIM-4D launcher set group (figure 1-35) consists
of the MAU-12B/A armament pylon, the inboard
AIM-4D launcher, and the bottom (lower) AIM-4D
launcher. The inboard launcher contains all the
electrical and electronic gear for both launchers.

The inboard launcher is bolted to the inboard side of
the MAU-12B/A armament pylon. The bottom launcher
is suspended from the MAU-12B/A ejector rack.
Ejector cartridges are not installed in the rack. The
AIM-4D launchers cannot be jettisoned. Electrical
connections for missile pre-launch signals are ac¬
complished through an umbilical connector from the
aircraft power source within the pylon. During ground
operations, the missile electrical connector is dis¬
connected to prevent inadvertent firing and must be
connected prior to flight. The AIM-4D is interlocked
with trailing edge flaps to prevent interference during
launch. The speed brakes may sustain damage if they
are extended during missile launch or jettison.

Note

•After T.O. 11L3-3-5-504, the AIM-4D
launcher is modified for AF Standard logic
and extended cooling. After this modifica¬
tion, the dash number of the Inboard Launcher
is changed from -120 to -130. Refer to T.O.
1F-4C-34-1-1A for additional information.

*After T.O. 11L3-3-5-507, the AIM-4D
launcher is modified for simplified launch
procedure. After this mod, the launcher is
marked with a decal ARM/START LAUNCHER
(selecting missile arm starts missile cooling)
and the dash number of the launcher is
changed to -140. Refer to T.O. 1F-4C-34-1-
1A for additional information.

LAU-7A/A MISSILE LAUNCHER

Refer to T.O. 1F-4C-34-1-1A.

AERO-3B MISSILE LAUNCHER

Refer to T.O. 1F-4C-34-1-1A.

1-90

Change 6

GUIDED MISSILE LAUNCHERS / F-4D /

INBOARD LAUNCHER.92 LBS

LOWER LAUNCHER.60 LBS

INBOARD ARMAMENT PYLON . . .264 LBS

T.O. 1F-4C-34-1-1

AGM-12 WEAPON SYSTEM (F-4D THRU BLK 33)

This section describes the AGM-12B/C/E guided
missile, launching system, associated equipment,
the cockpit controls and controlling procedures.

With respect to missile control and flight operations,
the missiles are nearly identical. The AGM-12B and
C missiles are both ground burst devices, with the
AGM-12C being considerably greater in weight and
explosive yield. The AGM-12E is basically the same
as the AGM-12C, except the -12E missile is an air-
burst, anti-personnel device.

Note

Refer to part 4 of this section for a descrip¬
tion of the AGM missiles.

MISSION

The AGM-12 missile and associated equipment pro¬
vides the radio-controlled, guided missile capability
to enhance the air-to-ground strike mission. With
the AGM-12 system energized, the AC begins an at¬
tack (dive or level) on the target and stabilizes the
airplane flight path directly toward the target. The
AC attempts to maintain a constant line-of-sight
(LOS) with the target throughout the missile run.

The missile fire signal is delivered by depressing the
bomb button (either cockpit), igniting the missile
liquid-fuel engine and the tracking flares. After en¬
gine burn-out (approximately 2.0 seconds) the AC
begins transmitting steering commands to the missile
receiver. The system transmitter emits the r-f
signals as the control selector handle is positioned
in combinations of left-right or up-down movements.
Hence, the AC directs the missile flight path in azi¬
muth and elevation, causing the missile (visible
tracking flares) to close on the LOS to the target.

CONFIGURATION AND SUSPENSION

AGM-12B MISSILE

A total of four AGM-12B missiles, one on each wing
station, may be carried and launched against tactical
ground targets. The inboard and outboard AGM-12B
suspension equipment for F-4D aircraft is shown in
figure 1-34. Each armament pylon receives the
LAU-34/A missile launcher. The branched wire
bundle from the armament pylon is attached to both
receptacles on the aft end of the launcher. The for¬
ward branch powers AGM-12B functions. (The aft
branch powers AGM-45 missile functions discussed
elsewhere in this section.) In a jettison situation,
only the missile is jettisoned. The LAU-34A remains
with the aircraft.

AGM-12C AND -12E MISSILES

A total of two AGM-12C or -12E missiles may be
carried, one on each inboard station. An AGM-12

relay panel, installed only in the inboard armament
pylon, relays the pre-arm and missile fire/release
signals from the cockpit. Hence the missile is loaded
directly on the pylon (MAU-12B/A) bomb rack. In
this case, the fire signal ejects the missile from the
rack and the missile engine ignites immediately after
ejection. A discussion of AGM-12 missile fire and
jettison procedures is provided later in this section.

LAU-34/A LAUNCHER (AGM-12B CARRIAGE)

In general, the launcher (figure 1-34) is responsible
for the proper dispersal of pre-heat, pre-arm, and
missile fire voltage. When the aircraft main bus sys¬
tem is energized, power is automatically directed to
missile components for warm-up purposes and the
system transmitter receives standby power. Thus,
the system is in a warm-up condition as soon as the
main bus system is energized.

When the AC selects the AGM-12 missile on the
weapon selector switch, relays in the launcher are
energized that unlock the pre-arm and missile fire
circuit. As the AC depresses (and holds) the bomb
button, the missile battery, gyro, pneumatic control
system, and warhead arming circuits are activated.
The missile battery builds up to power and closes a
relay in the launcher — completing the circuit be¬
tween the bomb button (depressed) and the liquid en¬
gine ignitor. The firing sequence takes approximately
2 seconds. The engine thrust force breaks the shear
pin in the forward retention mechanism (figure 1-34)
and the missile is free to launch. As the missile
separates from the aircraft, the umbilical breakaway
connector separates and the missile systems function
on battery power.

If the AGM-12B must be jettisoned, the jettison sig¬
nal energizes a cartridge in the launcher jettison gun
assembly. The force of the expanding gas from the
cartridge rotates the aft retention mechanism and
slides the missile rearward free of the launcher rail.
In this case, the missile freefalls in an inert state.
Only under the condition of a normal, powered launch
will the warhead become armed.

AIRCRAFT COMPONENTS

TRANSMITTER AND CONTROL SELECTOR
(AN/ARW-77)

1-93

T.O. 1F-4C-34-1-1

CONTROL HANDLE vs. CANARD DEFLECTION F-4D

by the transmitter. The transmitter circuits code,
amplify, and apply the commands to the lower UHF
antenna. Any one of the 24 command channels may
be used, depending upon the crystal installed in the
transmitter. The transmitter crystal assembly in¬
stalled must match that of the missile receiver.

The control selector (figure 1-38) receives power di¬
rectly from the transmitter and in turn applies com¬
mand output voltages to the transmitter circuit. With
the control handle in the neutral position, the system
continually emits a neutral or reference signal.
Movement of the handle causes signal changes with
respect to the reference signal. The amount of
change is directly proportional to handle displace¬
ment. A further discussion of control handle func¬
tions and the command link (adaptive control) system
is provided below.

Transmitter output to the missile is always emitted
through the lower UHF antenna on the nose gear door.
Any UHF radio transmission, while the AN/ARW-77
transmitter is in operation, is automatically emitted
through the upper UHF antenna, regardless of the
antenna switch position (UPR or LWR).

MISSILE CONTROL

ADAPTIVE CONTROL SYSTEM

The features of the adaptive control system may be
described by observing the functions of an individual
command. These functions (listed below) are directly

controlled by AC manipulation of the control handle in
the cockpit (figure 1-38).

a. Lead Pulse.

b. Variable Pulse Rate Frequency.

c. Auto-Check Command.

d. Memory Command.

When the AC deflects the control handle providing an
input voltage to the transmitter, circuits in the trans¬
mitter develop command pulses by repeatedly con¬
ducting and then deenergizing, applying and removing
voltage for transmitter pulse output. The net result
is that the missile canards momentarily deflect and
then return to neutral as each pulse is applied, con¬
tinuing the pulsating deflections as long as the handle
is displaced. The canards always deflect fully with
each pulse, regardless of the degree of control han¬
dle displacement. As an example, assume that the
AC — having launched a missile — applies an up cor¬
rection by moving the handle aft. Further, assume
that the stick is deflected about one-half travel at
time To, mid then returned to neutral at time Tl
(figure 1-37). In the figure, off time refers to the
time between pulses when the canards are neutral;
on time refers to pulse duration, which corresponds
to canard deflection time.

1-94

T.O. 1F-4C-34-1-1

F4D-34-I-226

Figure 1-38

to the LOS.) Hence, as the AC moves the stick, the
command must initially apply enough energy to rotate
the missile axis and change its course, and in some
measure account for the time lag in the command link
system. The lead pulse, that functions to quicken
missile response for the above reasons, is applied
for a longer period than subsequent pulses as figure
1-37 indicates. The width, or on time, of the lead
pulse is proportional to how rapidly the AC moves (or
accelerates) the stick to the desired position. A rapid
movement delivers a lead pulse of greater duration
than that of a gradual movement. This is in keeping
with the natural tendency to correct rapidly if the
AC notices a large error developing. Conversely,
the lead pulse function points out the necessity of us¬
ing gradual, smooth, control stick movements in in¬
stances where missile steering is extremely sensi¬
tive, or where steering errors are small.

As long as the control handle is held in the deflected
position, the pulse train continues. After the lead
pulse, subsequent pulses are short at first, increas¬
ing in duration (time) as the stick is held. This
means that the canards are deflected for increasing
periods of time with each pulse. If the AC increases
the amount of handle deflection, the amount of pulses
per unit of time increases, or in other words, the
frequency increases. Hence, the pulse rate frequency
varies proportionally with the amount of handle dis¬
placement. If the handle is displaced to full travel,
the pulse is continuous and canard deflection is con¬
tinuous. This is the same as stating (regarding fig¬
ure 1-37) that off time decreases and on time in¬
creases as handle displacement increases. The idea
is that the AC deflects the handle a specific amount
for an observed error. Then as the missile is ob¬
served to correct toward LOS at a satisfactory rate,
handle deflection may be reduced so that the amount
of error and command pulses delivered approach a
condition of balance. Small random errors are then
corrected by slight, smooth handle movement about
the neutral position.

As the handle is returned to neutral at time Tf, the
automatic check command is delivered. The check
pulse performs very nearly the same function as the
lead pulse, but the situation is reversed. As the mis¬
sile corrects and approaches the LOS, a force must
be applied to rotate and align the missile axis with
the LOS — preventing overshoot. Just as the lead
pulse, the pulse duration of the check command is
proportional to the rate of handle movement to neu¬
tral. If the AC notices an overly rapid rate of closure
with the LOS, he would naturally return the handle to
neutral at a rapid rate. Thus, the AC is able to re¬
duce lateral or vertical acceleration without handle
deflection in the opposite direction.

After control handle voltage is removed, the system
automatically generates small memory commands at
a constant rate. These commands will continue
throughout missile flight unless they are countered
by stick movement in the opposite direction. The
frequency of the memory commands is a function of
the amount and duration of the initial handle displace¬
ment. A small handle deflection held for a long dura¬
tion can develop the same memory as a large handle
deflection held for a short duration. The memory
circuits function to aid in overcoming natural forces
continually acting on the missile. In the example
command cited here, the up memory would serve to
compensate for further gravity drop.

In view of the above, one can visualize the system
when handle movements are made in directions other
than the cardinal ones. If the handle is moved to de¬
liver an up-right command for example, the com¬
mand sequence in figure 1-37 is applied in both up
and right directions simultaneously. The point to be
made is that the AC need not restrict control move¬
ment to cardinal directions only, but may use com¬
binations of the cardinal commands and vary their
magnitude.

CONTROL CONSIDERATIONS

The above discussion treats the system somewhat
ideally for purposes of demonstration. In practice,
there are several more things to consider. The AC
must establish the desired LOS with the wings level,
applying enough forwai'd trim to counteract the ten¬
dency for the nose of the aircraft to rotate as velocity
during the dive increases. Remember that the mis¬
sile gyro is uncaged while the missile is still on the
launcher, and that the gyro establishes a vertical
reference relative to the position of the aircraft.
Thus, if the aircraft is in a 45° left bank at launch
and subsequently rolled level after launch, an up-
command will result in the missile steering up-left.

When firing tire liquid engine, the missile is plainly
visible at launch. Engine burnout is identified by a
puff of white smoke. The AC must ensure no com¬
mands are issued until after engine burnout. The AC
will obtain best results if he can avoid the natural
tendency to fix his vision on the missile flares after
launch. Rather, keep the eyes fixed on the target
(or impact point of the target) and view the missile
flares through the peripheral vision. The picture is
similar to the pipper light floating on the wind screen.
This procedure will help maintain a steady LOS.

1-95

T.O. 1F-4C-34-1-1

In most cases, the missile appears below the tar¬
get and to the left or right, depending upon the wing
station used. If the missile is low, the first feasible
command is the up command to initiate the upward
correction, and to help counteract further sink due to
gravity by establishing up memory. At the lower re¬
lease angles, the effect of gravity will be greater. If
the missile is initially high before any commands are
issued, allow gravity to correct the elevation error.

A down command with down memory, plus the effect
of gravity, is sure to result in overshoot below the
LOS. With all systems functioning normally, the
command link system is most sensitive during the
first few seconds after engine burnout. Hence, use
smooth control action to establish a desirable cor¬
rective trend toward LOS, rather than attempting to
eliminate all sources of error immediately. Missile
steering tendencies will vary; that is, some missiles
will be more sensitive than others. When applying
the initial command, however, all missiles should be
regarded as very sensitive; it is easier to add more
handle displacement than to correct an over-con¬
trolled missile.

The AC can get an idea of how much handle deflection
is needed by observing missile trend. To illustrate,
suppose the flares are observed to move from left to
right toward the LOS at a rapid rate. At the instant
the flares move into and conicide with the LOS, the
apparent error is zero; but the error trend remains
very large since the angle between the missile axis
(or flight path) and the LOS is relatively large. In
this case, considerable control movement, with proper
lead, would be necessary to avoid overshoot. How¬
ever, if the missile is considerably wide by generally
holding position relative to the LOS, the missile axis
may be considered to be nearly parallel to the LOS.

In this case, a lesser control deflection is necessary
to divert the missile and the AC uses smooth control
input, varying handle deflection only to establish a
controllable correction rate.

H the missile can be established at a point close (and
parallel) to the LOS early in flight, there should
never be any need for large, rapid, control handle
movements. In fact, during the early phase of mis¬
sile flight, the AC will usually have to use conscious
effort to avoid overcontrol. With the adaptive sys¬
tem, a small degree of handle displacement held for
a longer time produces the same effect as a full
deflection for a very short interval. The former is
by far the more desirable, however, since the trend
of missile correction is more easily judged. The
continuing effect of gravity must be kept in mind, and
possibly used to an advantage. As dive angle increases
that component of gravity that tends to pull the mis¬
sile down from the LOS becomes less. However, if
the missile steers slightly high, up memory will
probably not be sufficient to continually hold the mis¬
sile high and gravity may be used to make tire neces¬
sary correction. The AC must avoid anticipating the
impact, and continually fly the missile until impact
is observed.

Roll Reference Shift

The description of the AGM-12 gyro system (part 4)
points out that at supersonic velocity, the missile roll

rate is an average 500° per second. Further, the
pickoff brushes in the missile gyro are biased 50° to
compensate for 0.1 second time lag in the command
link system. As the missile decelerates, however,
and approaches the transonic region (Mach 1.1 to
0.9), the lift force at the bent wing tips increases
rapidly and causes a rapid increase in roll rate.
Missile roll can increase to an approximate maxi¬
mum rate of 1000° per second. Thus, maximum
shift becomes approximately 100° which means that
the original 50° bias no longer compensates for the
command lag and missile response would occur 50°
counterclockwise from the desired response. It is
difficult to predict the point at which roll reference
shift begins since one must consider factors such as
launch angle, launch velocity, and individual control
technique which directly effects the rate of missile
deceleration. If the technique of steering the missile
along the LOS is executed properly, the buildup rate
of roll reference is very slow and actual observance
of the shift phenomenon is impossible.

A rule-of-thumb method has been devised that --
knowing a desired time of flight (Tf) — may be used
to determine launch altitude (AGL) for a specific dive
angle. The method makes use of a factor which cor¬
responds to a specific Tf as follows:

Factor

0.3

10 sec.

0.4

15 sec.

0.5

20 sec.

0.6

25 sec.

0.7

30 sec.

For example, assume the AC begins the dive on tar¬
get, establishes LOS, and observes the dive angle to
be 35°. If the 20 sec. Tf is planned, the factor of 0.5
is applied (above) so that launch altitude (AGL) is:

0.5 x 35° dive = 17.5 thousand feet AGL.

If target altitude is 1500 feet MSL, indicated launch
altitude becomes:

17.5 +1.5 = 19.0 thousand feet.

The above method is accurate (AGM-12B missiles)
within ± 2 seconds for dive angles with 15° and 45°,
and launch airspeeds between 300 and 600 KTAS.

Offset Deliveries

All previous considerations stated apply to offset
deliveries. In this delivery, the LOS continually
rotates. For example, if the target is approximately
10“ right at launch, it may move to a relative position
of 40° right at impact. In view of the shift phenom¬
enon discussed, the target must always be offset to
the right. In a shift environment, a right command
would result in an up-right response, a relatively
easy situation to control. A left command, however,
would result in a down-left response, which is nearly
impossible to control in an offset mode. In any de¬
livery situation, the rate of LOS rotation can be re¬
duced by reducing airspeed to as low a rate as the
situation permits.

1-96

T.O. 1F-4C-34-1-1

COCKPIT CONTROLS

The F-4D aircraft pedestal panel is shown in figure
1-17. The switches provide the individual station
select capability. The following discussion considers
all AGM-12 missile functions.

WEAPON SELECTOR KNOB

On the pedestal panel, the AC selects the AGM-12
position with either missile above. This selects the
required firing system by closing relays in the
launcher (AGM-12B) or in the inboard pylon AGM-
12C relay panel. In this function, the intervalometer
is placed in a singles output mode so that missile fire
voltage is directed only to the selected wing station.
Finally, selecting AGM-12 closes one portion of the
transmitter-activate circuit; the transmitter may be
tested after energizing the master arm switch.

MASTER ARM SWITCH

Placing the master arm switch to ARM energizes the
bomb button transfer relays, which will direct bomb
button voltage into the conventional weapons circuits.
The transfer relays will not energize, however, if
any of the special weapons release relays (5) are
energized. Thus, either the DCU-94/A master re¬
lease lock, or the station select (all 5), or the con¬
sent switch must be off. Selecting ARM immediately
closes the bomb button/transmitter-activate circuit.
If, at this point, the AC depresses the bomb button,
the system transmitter begins the 50 ± 10 second
cycle. Hence this method may be used to test (while
airborne) the aircraft portion of the command link
system. The station select buttons must remain off
to avoid firing the armament.

Note

* For transmitter ground test purposes, a
Gam-Aux switch is located in the nose wheel
well.

•To perform any AGM-12 functions that are
executed through the bomb button, the deliv¬
ery mode selector must be positioned on
DIRECT.

• The Good Guidance Monitor (GGM) performs
a safing function in the AGM-12E fuzing sys¬
tem (refer to section 4 of T.O. 1F-4C-34-1-
1A). In F-4D aircraft, the function is acti¬
vated during missile flight by pulling the
armament power circuit breaker (6E), No. 2
panel in the rear cockpit. (See T.O. 1F-4C-
2-18A.) Pulling this circuit breaker deener¬
gizes AN/ARW-77 transmitter output.

STATION SELECT BUTTONS

These controls (figure 1-17) are pushbutton switches
containing green and amber indicator lights inside the

button housing. The green light simply indicates that
a specific button has been depressed. Therefore, if
one or more buttons are on, the green light(s) will
illuminate immediately as the ac bus system is ener¬
gized. Both lights are tested through the test control
on the right console.

Each button selects a specific station by energizing
the corresponding station select relay, which must be
energized to get launch voltage to the missile. The
amber light, however, serves several purposes.

With a specific button depressed, the light indicates:

1. That the pylon wire bundles are properly in¬
stalled for the specific station selected. In the
case of the AGM-12B, the light indicates that
the LAU-34/A launcher bundle is plugged into
the proper pylon receptacle. With the AGM-
12C and -12E aboard, the light indicates that
the AGM-12C relay panel is properly connected
into the aireraft/AGM-12 circuits.

2. That the station select relay is closed, which
connects bomb button output to missile launch
circuits.

3. That the master arm switch is positioned to
ARM, which closes another interlock in the
bomb button circuit.

Thus, the amber light simply indicates that the air¬
craft is properly configured for the weapon selected,
and provides a complete launch-ready signal. When
the bomb button is depressed, launch voltage is di¬
rected through each station relay in the following
order:

1. Left OUTBD (LO)

2. Left INBD (LI)

3. CL

4. Right INBD (RI)

5. Right OUTBD (RO)

In order to fire an AGM-12B missile from the RO
station, all of the other station select switches must
be off. To fire the LI station missile, only the LO
station must be off. The CL button is included even
though this station is not AGM-12 capable. This
merely points out that it is impractical to energize
all stations at once with several AGM-12 missiles
aboard. Rather than commit the above order to mem¬
ory, the AC may simply select one station at a time,
and after firing the selected missile, place that sta¬
tion off before selecting the next.

JETTISON CONTROLS

The AGM-12C or -12E missile is jettisoned (ejected)
directly from the MAU-12 rack in the armament py¬
lon. The AGM-12B missile is jettisoned (kicked)
rearward by the LAU-34/A launcher jettison gun as¬
sembly.

1-97/(1-98 blank)

T.O. 1F-4C-34-1-1

PART 3 DESCRIPTION

TABLE OF CONTENTS

MISSION DESCRIPTION (F-4E)

Dive Bombing.1-100

Direct Bomb Mode.1-100

Rocket Launch.1-100

Gun Firing.1-100

Level Bombing.1-102

Ripple Release Bombing.1-102

Low Drag Bomb Delivery.1-102

Fire Bomb Delivery.1-102

CBU Delivery.1-102

High Drag G.P. Bomb Delivery.1-104

Leaflet Bomb Delivery.1-104

Flare Dispensing.1-104B

Loft Bombing.1-105

AIRCRAFT WEAPON SYSTEM CONTROLS
(F-4E) (Before T.O. 1F-4E-556)

Delivery Mode Selector Panel.1-106

Station and Weapon Select Panel .... 1-106

Trigger Switch.1-111

Bomb Button.1-111

Weapon Release/Launch Modes.1-112

AIRCRAFT WEAPON SYSTEM CONTROLS
(F-4E) (After T.O. 1F-4E-556)

Air-To-Ground Weapons.1-114

Automatic WPNS Release Unit (AWRU) . 1-114C

Air-To-Air Weapons.1-114C

Weapons Release Computer Set.1-114G

Lead Computing Optical Sight.1-118

Loft Bombing Equipment.1-121

WEAPON DELIVERY MODES (F-4E)

Air-to-Air Gunnery.1-123

Nose Gun System, M61A1.1-125

Direct Delivery Mode.1-128A

Dive Toss Bombing Mode.1-128

Dive Laydown Bombing Mode.1-132

Laydown Bombing Mode.1-133

Offset Bombing Mode.1-134

Target Finding Mode.1-140

LABS/WRC S Bombing Mode s.1-141

FIRE CONTROL SYSTEM. AN/APQ-120
(F-4E) Refer to T.O. 1F-4C-34-1-1-1

JETTISON CONTROLS (F-4E)

Emergency Jettison.1-144

Selective Jettison.1-144

SUSPENSION EQUIPMENT (F-4E)

BRU-5/A (AERO-27/A) Bomb Rack. . . 1-146

Armament Pylons.1-146B

Multiple Ejector Rack (MER).1-150

Triple Ejector Rack (TER).1-151

LAU-34/A Launcher.1-151

Rehoming MERS and TERS.1-151

Missile Launchers.1-155

AGM-12 WEAPON SYSTEM (F-4E)

Mission.1-156

Configuration and Suspension.1-156

Aircraft Components.1-156

Missile Control.1-157

Cockpit Controls.1-159

COMBAT SUPPORT EQUIPMENT

Optical Sight Camera, KB-25/A .... 1-160A

AGM-45 WEAPON SYSTEM (F-4E)

Refer to T.O. 1F-4C-34-1-1-1

AGM-65 WEAPON SYSTEM (F-4E) Refer
to T.O. 1F-4C-34-1-1-1

KMU-353A/B (MK 84 EO) GUIDED
WEAPON Refer to T.O. 1F-4C-34-1-1-1

MARK 1 MOD 0 GUIDED WEAPON SYSTEM (F-4E)
Refer to T.O. 1F-4C-34-1-1-1

RADAR WARNING SYSTEM, AN/APR-36/37 (F-4E)
Refer to T.O. 1F-4C-34-1-1-2

TISEO (F-4E) Refer to T.O. 1F-4C-34-
1 - 1-1

INTERROGATOR SET (AN/APX-81)

Refer to T.O. 1F-4C-34-1-2 and
T.O. IF-4C-34-1 -1CL-1

Change 9

1-99

T.O. 1F-4C-34-1-1

—

MISSION DESCRIPTION (F-4ET

DIVE BOMBING

Dive bombing with the F-4E aircraft can be per¬
formed with the aid of the weapons release computer
set (WRCS), or by the DIRECT release mode. The
WRCS delivery mode normally associated with the
dive bombing mission is the DIVE TOSS bombing
mode (figure 1-39). When the DIVE TOSS bombing
mode is used, the weapons release computer solves
the bomb ballistics problem for various release
speeds, altitudes, and dive angles, and automatically
releases the bomb. Therefore, mission planning is
reduced to obtaining the drag coefficient of the bomb
and determining a safe recovery altitude. Wind cor¬
rection for the low drag bombs is normally not re¬
quired. Refer to wind correction.

Note

Neutral rudder trim should be accomplished
at the planned delivery speed. Since the turn
and slip indicator in the aft cockpit is more
sensitive, the pilot should assist the AC by
calling the indicator display.

For any given dive angle, the bombing tables in T.O.
1F-4C-34-1-2 assume a normal G-loading which can
be obtained only when a wings-level, straight line
flight path is maintained prior to release. The pipper
should be allowed to walk toward the target or aim-
point and should arrive when the aircraft is at the
release altitude and airspeed. The roll tabs on the
optical sight should be used to maintain wings-level
flight. If radar lockon can be obtained, the range
bar may be used to establish the slant range.

DIRECT BOMB MODE

Several factors must be considered when determining
an indicated release altitude: altimeter position error
altitude loss during pullout, minimum aircraft ground
clearance; altimeter lag; and target elevation. The
altimeter is set according to target pressure reduced
to sea level (target altimeter setting). Immediately
following bomb release, a 4 G pullout is initiated.

The acceleration rate is 4 G obtained 2 seconds after
release. If buffeting is encountered, the buffet bound¬
ary is maintained until the desired climb attitude is
obtained. When the DIRECT delivery mode is used,
mission planning becomes more detailed. The dive
bombing tables provide trajectory data for the vari¬
ous parameters associated with the delivery. Con¬
sistency in the all-important roll-in parameter can¬
not be overemphasized. The parameters of altitude,
airspeed, distance from target, and power setting
are preplanned to place the aircraft at a predeter¬
mined release altitude and distance from target, with
a predetermined bomb release velocity and attitude to
effect an accurate hit. Because of the longer periods
of wind effect on the trajectory of the bomb, it is also
important that the aircrew have knowledge of the
magnitude of wind effect and, primarily, the wind
velocity at release altitude.

Selecting the direct delivery mode enables the lead
computing optical sight to be used as a fixed sight
reference that can be depressed from zero mils to
245 mils below the fuselage reference line. The
actual sight setting is obtained by adding the aircraft
zero sightline angle of attack to the value obtained in
the bombing tables (T.O. 1F-4C-34-1-2). The optical
sight is used in conjunction with the altimeter, and
the calibrated airspeed indicator to determine the re¬
lease point.

ROCKET LAUNCH

The DIRECT delivery mode is used to fire the 2.75-
inch folding fin aircraft rocket (FFAR). The optical
sight is operated in the A/G mode. The sight de¬
pression angles are presented in the rocket launch
tables as a function of angle of attack rather than the
depression angle from flight path. Only the RKTS &
DISP SINGLE position should be used when firing the
rocket launchers to ensure complete fire-out of all
rockets.

Note

If RKTS & DISP RIPPLE is selected, the
launcher will not fire-out completely be¬
cause the firing pulse from the aircraft in-
tervalometer is not of sufficient length to
completely fire-out the launcher intervalom-
eter.

Fuze arming is not a consideration for rocket launch I
except when using the WDU-4A/A Flechette Warhead; I
refer to the confidential supplement for release con- I
siderations, section V. Safe escape considerations
are somewhat different in that the aircraft is flying
toward the frag envelope and possible secondary ex¬
plosions from the target. The safe escape tables in
section VI do not consider terrain avoidance nor
secondary target explosions. The effect of wind is
less than for bombs because of the shorter time of
flight. The rocket launch tables presented in T.O.
1F-4C-34-1-2 are valid for all rocket launchers and
type of suspension equipment used. Separate launch
tables are required for the various categories of
warhead used with the 2.75-inch rocket motor.

GUN FIRING

When firing the SUU-16/A gun pod or the M61A1 nose
gun in an air-to-ground environment, either the OFF
or DIRECT position should be selected on the delivery
mode selector panel to orient the optical sight with
the fuselage reference line (refer to optical sight
functions, figure 1-48). Safe escape considerations
when firing the 20mm gun must include terrain
avoidance, ricochet, and secondary target explosions.
The delivery considerations for firing upon a ground
target are generally the same as for bombing and
rocket firing. Wind and sight depression corrections
is less because of the projectile shorter time of

1-100

Change 5

T.O. 1F-4C-34-1-1

DIVE DELIVERY

RELEASE ALTITUDE
START PULLOUT

ALTITUDE TLOST

MINIMUM ALTITUDE
AGL

RELEASE

ir^ 1 . *A V

ALTITUDE

RELEASE PATTERN
OF ONE TUBE

F4E-34-I- 302

Figure 1-40

1-101

T.O. 1F-4C-34-1-1

flight. Like the rocket launch tables, the sight set¬
ting is given as a function of gross weight. Refer to
the description of the SUU-16/A gun pod and the
20mm ammunition. When firing the guns in air-to-
air gunnery, the lead computing optical sight set
(AN/ASG-26) functions to position the sight reticle in
azimuth and elevation and satisfy the geometry of a
lead pursuit course. (Refer to Air-to-Air Gunnery,
this section.)

LEVEL BOMBING

Level bombing (figure 1-40) is a special case of dive
bombing where the dive angle is zero; the delivery
parameters are basically the same. The approach
to the target is performed at a constant altitude,
wings level, and at a stabilized airspeed. After bomb
release, the aircraft may continue the approach
course and speed or perform the required escape
maneuver. The weapons release computer set
(WRCS) provides a variety of delivery modes that can
be used for level bombing; dive toss (dive-level ma¬
neuver), dive laydown, laydown, or offset bombing.
Refer to Weapon Delivery Modes this section. The
most sensitive parameters that affect bombing ac¬
curacy are the release altitude above target and pitch
attitude. Refer to Altimeter Position Error, sec¬
tion V. The method used to correct for wind effects
is determined by the method of target tracking
(crabbed or drifting) and the type of weapon (high
drag or low drag). Refer to Wind Correction, sec¬
tion V.

RIPPLE RELEASE BOMBING

Ripple release bombing tables are provided in T.O.
1F-4C-34-1-2. Ripple release (figure 1-41) (dive or
level) delivery is identical to the single release with
the following additions:

a. Safe escape and dive recovery must be based on
the release altitude of the last bomb.

b. The sight setting or bomb range is computed to
place the center of the impact pattern on target.

c. Wind correction is based on the time-of-fall of
the first bomb released.

d. The minimum release altitude for a level ripple
release is based on a straight ahead escape.

When bombs are ripple released (BOMBS TRIPLE
mode), the release advance control can be used with
one of the WRCS delivery modes to place the center
bomb on target. The release parameters are com¬
puted for a single bomb release.

LOW DRAG BOMB DELIVERY

Level bombing tables are provided in T.O. 1F-4C-
34-1-2. Lower release altitudes can be used (i.e.,
500 feet) if full military power is selected and a 4.0

G pullup is initiated immediately after bomb release
to attain a 20° to 30 climbing attitude. Refer to Safe
Escape, section V. Crosswind correction is not re¬
quired if the aircraft is crabbed to maintain a ground
track through the target. Rangewind correction is
not required if the bomb is released at a ground speed
that is equal to the preplanned true airspeed. Refer
to Wind Correction, section V.

Dive bombing tables are provided in T.O. 1F-4C-34-
1-2 for all the low drag bombs and the practice
bombs. Refer to safe escape, the fuze arming charts,
and the dive recovery chart to determine the mini¬
mum release altitudes.

FIRE BOMB DELIVERY

Level bombing and dive bombing tables are provided
in T.O. 1F-4C-34-1-2 with dive angle from 0 to 45 .
The sight depression angle given in the tables is com¬
puted to place the fire bomb on target; when it is de¬
sirable for the fire bomb to hit short of the target,
the distance must be estimated or the sight setting
recomputed using the sight depression charts in sec¬
tion VI. Wind corrections can be applied in the same
manner as for the low drag bombs. Refer to wind
correction, section V. The dive recovery charts
must be used to determine the minimum release al¬
titude.

WARNING

DO NOT FLY through FIRE BOMB SMOKE
within 20 seconds of burst as a compressor
stall or flameout could occur.

CBU DELIVERY

The direct, dive laydown, laydown, or the offset
bombing delivery mode may be used to deliver the
CBU munition with either a single release or ripple
release. Low-level bombing, using the CBU muni¬
tion consists of a low-level or low-angle approach to
target at the predetermined speed and altitude above
target. Crosswind correction is applied (in addition
to crabbing the aircraft) by offsetting the flight path
parallel to, and upwind of the no-wind ground track.
Flight path offset, to correct for crosswind, is re¬
quired by the high-drag CBU munition because of its
longer time of flight. The optical sight establishes
the release point when the direct delivery mode is
used. The release point is automatically computed
and release is automatically initiated by the weapon
release computer set when the dive laydown, lay-
down, or offset bombing mode is used to deliver the
CBU munition. Rangewind correction may be ignored
for the CBU delivery. The bombing tables provide
the sight depression angle from flight path that will
place the first bomblet 500 feet short of the target.
When it is desirable to change the impact point of the
first bomb, the sight depression charts in section VI,
must be used to establish the sight depression from
flight path.

1-102

RIPPLE RELEASE

DIVE DELIVERY

R] Range of First Bomb.

Rfsj Range of Last Bomb.

0 Dive Angle.

A] Release Altitude of First Bomb.

Al Altitude Lost During Pullout.

A^ Release Altitude of Last Bomb.

N Number of Bombs Released.

Rp Range from Release to center of pattern
SD Sight Depression.

Time of fall of first bomb.

IR Release Interval in Sec.

PL Pattern Length

1. PRIOR TO TRP, SELECT LOFT DELIVERY MODE AND SET UP THE MULTIPLE WEAPON RELEASE MODE.

2 WHEN OVER TRP THE AC DEPRESSES AND HOLDS THE BOMB RELEASE BUTTON TO START THE PULLUP TIMER, THE PULLUP LIGHT WILL
ILLUMINATE AND THE HORIZONTAL AND VERTICAL POINTERS ON THE ADI WILL CENTER.

3 WHEN THE STEADY TONE SOUNDS AND THE PULLUP LIGHT GOES OUT, ADVANCE THROTTLES TO FULL MIL POWER AND BEGIN PULLUP. FLY
TO KEEP ADI POINTERS CENTERED UNTIL BUFFET ONSET, THEN FOLLOW BUFFET BOUNDARY.

4 WHEN THE SELECTED RELEASE ANGLE IS ACHIEVED, THE PULLUP LIGHT WILL ILLUMINATE, AND THE STEADY TONE WILL STOP THE AC WILL
CONTINUE TO HOLD THE BOMB RELEASE BUTTON DEPRESSED UNTIL THE LAST BOMB IS RELEASED.

LAST BOMB IS RELEASED, INITIATE A WINGOVER TO ACHIEVE A 120 DEGREE TURN WHILE DIVING TO ESCAPE AT MINIMUM ALTITUDE

T.O. 1F-4C-34-1-1

MK 24 FLARE PROFILE

Release

D Minimum release altitude AGL required to provide
flare burnout.

E Vertical drop prior to flare ignition.

E Ejection fuze delay time.

D Ignition fuze delay time.

El Flare Burning Time:

a. Mod 3: 180 sec.

b. Mod 4: 198 sec.

B Desired flare burnout height AGL.

Q Horizontal flare travel prior to ignition.

_4C-34-1-l-(44)

Figure 1-42

penser is not modified with tube extensions to pre¬
vent bomb hang-up and possible subsequent early
detonations.

WARNING

Do not release bombs from unmodified SUU-7
dispensers (without tube extensions) while the
aircraft is in other than wings level stabilized
flight.

HIGH DRAG GP BOMB DELIVERY

The high drag GP bombs can be delivered from alti¬
tudes between 100 feet to 3000 feet depending upon
the bomb used, the fuzing limitation, fragmentation
envelope and dive angle. The high drag characteris¬
tic provided by the retarder tail fin assembly re¬
duces the bomb range and increases the bomb time
of fall and impact angle. Single release and ripple
release bombing tables are provided in T.O. 1F-4C-
34-1-2.

WARNING

DO NOT FLY over or near burst area within
20 seconds of detonation as aircraft damage
can result from flying debris. During train¬
ing missions, at least 20-seconds spacing be
tween aircraft must be observed when inert
or sand filled bombs are released. In the
training situation, observing the 20-second
spacing between aircraft prevents a bomb-
to-aircraft collision in the event a bomb re¬
leases low drag and ricochets into the air
after impact.

WARNING

When the dive delivery is used, a straight
line flight path should be maintained during
the release and for 2 seconds after the re¬
lease; the minimum release altitude should
be planned accordingly.

CBU DELIVERY USING THE SUU-7 DISPENSER

When a dive delivery is used for CBU series weap¬
ons using the SUU-7 dispenser, a straight line flight
path should be maintained during the release and for
2 seconds after release. The minimum release alti¬
tude should be based on altitude lost during recovery
plus altitude lost during the 2-second stabilized dive
after release. This procedure is necessary to pre¬
vent voids in the bomb impact pattern whether using
dispensers with or without modified tube extensions.
The above procedure must be used when the dis-

MK82 (SNAKEYE I) AND M117R HIGH/LOW DRAG
OPTION, IN-FLIGHT SELECTIVITY

The MK 82 (Snakeye I) and M117R GP bombs can be
released in a low drag configuration (retarding fins
remain closed) or a high drag configuration (retard¬
ing fins open after release) provided arming wire
routing is accomplished during loading to provide
these options. The high or low drag configuration is
selected in flight through the arm nose tail switch on
the multiple weapons control panel. Refer to Arm¬
ing Wire/Lanyard Routing, part 4, for detailed in¬
formation concerning the required arming wire con¬
figuration for this capability.

For a high drag release using the in-flight option,
the NOSE & TAIL position is selected on the arm
nose tail switch. The NOSE position is selected for
a low drag release with only the nose fuze initiated.
After T.O. 1F-4-805, the TAIL position may be
selected for a high drag release with only the tail
fuze initiated.

1-104

Change 5

T.O. 1F-4C-34-1-1

WARNING

Since certain mechanical and human errors
inherent with this type delivery option can
result in hazardous or degraded reliability
situations, the operational commander should
consider the following notes and warnings
which point out the possibility of self in¬
flicted damage, injury to friendly ground
forces, single fuze reliability, and delivery
accuracy degradation before approving this
option for operational use.

Note

With the approved arming wire routing for
the in-flight high/low drag option, single fuze
reliability (nose fuze only) is available with
the low drag option. Dual fuzing reliability
(nose and tail) is available with the retarded
higli drag option if the high drag bomb time
of fall exceeds 6.6 seconds. If the high drag
bomb time of fall is less then 6.6 seconds,
only FMU-54 tail fuze arming is available.
Single fuze reliability (tail fuze only) is
available with the high drag option when the
arm nose tail switch is positioned to TAIL.

WARNING

With current arming time tolerances, the
minimum bomb time of fall to provide time
for the fuzes to arm is 6.6 seconds for the
nose fuzes and 2.8 seconds for the tail fuze
(high drag arming only).

* Dive Releases. For planned high drag dive
releases, the release altitude must not ex¬
ceed 1000 ft AGL.

* WRCS Dive-Toss Releases. For planned high
drag dive toss releases, the pickle altitude
must not exceed 1000 ft AGL.

* Level Releases. For planned level releases
of high drag weapons and a straight and level
escape maneuver, the release altitude must
not exceed 250 ft AGL. This restriction does

not apply for a single, pairs, and salvo type
release if a 4G wings level pullup or a 4G
60° banked turn escape maneuver is executed
immediately after release.

Note

None of the foregoing restrictions apply if
the planned high drag bomb release altitudes
exceed the minimum release altitudes that
are required for safe escape for low drag
MK 82 bombs.

WARNING

* There is also a possibility of the delivery
aircraft suffering self-inflected fragment
damage if an intended high drag bomb re¬
leases low drag during a close-in attack con¬
dition, and for some reason detonated at
initial impact. To provide an additional
margin of safety in this event, the pilot
should execute a 4-G pullup or a 4-G, 60°
banked escape maneuver immediately after
release.

* Minimum release altitudes with respect to
fragment envelope clearance should be ob¬
served even if the bomb is released SAFE.
This would protect the aircrew in the event

of an arming wire hang-up, solenoid malfunc¬
tion, etc., resulting in an arming wire being
extracted and the bomb becoming fully armed.

Change 9

1-104A

T.O. 1F-4C-34-1-1

Note

WARNING

If high drag ripple releases of the M117R or
MK 82 Snakeye I bombs are anticipated using
the in-flight high/low drag option selectivity,
the munitions must be loaded in the config¬
uration specified in T.O. 1F-4C-1 for this
type release.

LEAFLET BOMB DELIVERY

The weapon release computer set can be used to lo¬
cate the target and automatically release the leaflet
bomb. The offset bombing mode, the laydown mode,

the dive laydown, or the direct delivery mode can be
used for leaflet bombing. The Ml29El leaflet bomb
is released from altitudes of 4000 feet through
11, 000 feet. The bombing table states the bomb time
of flight and range from release to burst for a given
level flight release true airspeed and release alti¬
tude above target. The time of flight is used to set
the mechanical time delay fuze for a 300-foot detona¬
tion. The bomb range is used to estimate the re¬
lease point. Various wind effects on the bomb prior
to burst will be a function of wind velocity and bomb
time of flight. The wind effect on the leaflets after
detonation and during the descent is difficult, if not
impossible, to predict.

FLARE DISPENSING

The SUU-25A/A, B/A, C/A flare dispenser is used
to deliver theMK 24flares. The delivery aircraft ap¬
proaches the target in level flight at the preplanned
release altitude. The MK 24 flare profile and pa¬
rameters are illustrated in figure 1-42. Release
airspeed is not a critical parameter. Release alti¬
tude is critical only when it is desirable to have flare
burnout above the ground. The flare dispensing table,
T.O. 1F-4C-34-1-2 provides the minimum release

1-104B

Change 9

T.O. 1F-4C-34-1-1

altitude AGL for flare burnout at impact. The de¬
sired burnout altitude AGL must be added to the
minimum release altitude AGL to determine the
actual release altitude AGL. The flare dispensing
table also provides the horizontal distance traveled
and vertical drop of the flare prior to ignition. The
flare ejection fuze delay time and the flare ignition
fuze delay time is set according to mission require¬
ments and the data on the flare dispensing table. To
properly position the flare at ignition, range-wind ef¬
fect and crosswind offset (ft) may be determined by
multiplying the rangewind or crosswind component
(kts) times 1.7 times the sum of the ejection and igni¬
tion fuze delay settings.

LOFT BOMBING

Note

Also refer to LABS/WRCS Bombing Modes,
this section.

The loft bombing mode combines the use of the multi¬
ple weapons release system (MWRS) with the attitude
reference and bombing computer set (ARBCS). The
purpose of the loft bombing mode is to provide a rip¬
ple release capability of GP bombs from low altitude
with a minimum of aircraft exposure time to ground-
fire and without a target fly-over. This is accom¬
plished as illustrated in figure 1-41.

During mission planning, an IP (Identification Point)
is selected on the target map, or photos, that is lo¬
cated near and on course to the target; the pullup
point is established; the release angle of the first and
last bomb, the pattern length of the bombs, and the
pullup timer setting are also defined.

Prior to the bombing run, the pedestal panel is set
for a bombs ripple release with the master arm
switch in ARM and the stations selected; the delivery
mode selector knob is positioned to LOFT. The
LABS bomb release angle computer is set for a low
angle (loft) release.

Note

The AC may use the Fast Erect switch to
momentarily cage the AN/AJB-7 gyros and
correct any gyro precession during the
level, constant speed target run-in. Refer
to LABS/WRCS Bombing Modes, this section.

When LOFT is selected and the optical sight is op¬
erated in the A/G mode, the sight is pitch stabilized
with reference to the horizontal platform and can be
manually depressed. The sight is not drift stabilized
The reticle light will follow the pullup indications

(pullup light ON - reticle light ON, pullup light OFF -
reticle light OFF). Either bomb button (front or rear
cockpit) is depressed over the IP; this starts the
pullup timet countdown. Bomb button power also
energizes relays which illuminate the pullup light,
and which move the horizontal and vertical pointers
of the ADI into view over the center of the sphere.

The vertical pointer initially indicates roll flight
deviations and the horizontal pointer shows devia¬
tions from 1.0 G flight. The appearance of the point¬
ers indicates that the ARBCS has properly switched
into the LOFT bombing function. At the end of the
total time interval, pullup voltage is applied to the
tone generator producing a continuous audible tone.
The pullup light circuit is deenergized and the light
goes off. These are the direct indications to begin
pullup. The AC should select MIL power and begin
rotation into the pullup maneuver. As the timer com¬
plete contacts close, voltage is applied to one side
of the low and high angle release switches which are
not yet energized. Relays in the flight director bomb¬
ing computer are energized to start the G program¬
mer. The ADI horizontal pointer now indicates G
error based on 4 G obtained in 2 seconds. The hori¬
zontal pointer deflects upward unless the AC begins
pullup.

When the aircraft reaches the preset pitch attitude,
the release angle switch closes and applies the re¬
lease signal. As release voltage is applied, the tone
generator is deenergized, the timer is reset, and
the pullup light illuminates. The AC continues to hold
the bomb button depressed and the G program will con¬
tinue to be displayed by the ADI horizontal pointer as
an aid in completing the maneuver. The vertical
pointer, however, is deflected out of view at re¬
lease. When the AC releases the bomb button, all
bombing voltage is removed and the horizontal
pointer deflects out of view, and the pullup light goes
off.

Note

During the LOFT mode, once the bomb but¬
ton is depressed, it must remain depressed
until final bomb release. If the bomb button
is released before the first bomb is re¬
leased, a lockout circuit is energized and
the run cannot be continued by depressing
the bomb button. To overcome the interlock,
the bomb mode selector knob must be posi¬
tioned out of the LOFT function and then re¬
turned to LOFT.

Change 7

1-105

T.O. 1F-4C-34-1-1

mode. The horizontal needle on the ADI sphere will
program 3.5 G in 1.5 seconds (not 4.0 G In 2 seconds
as for the loft mode) until approximately 38° pitch
attitude is achieved. Therefore, the ADI cannot be

used above 38° when the LADD bombing system is
used to accomplish the loft delivery, the aircraft ac
celerometer must be used to establish the pullup ac¬
celeration until buffet onset.

AIRCRAFT WEAPON SYSTEM CONTROLS (F-4E) BEFORE T.O. 1F-4E-556

In order to simplify a description of weapons control,
the aircrew might consider the aircraft in terms of
three weapons categories: nuclear system, air-to-
air missile system, and multiple weapons system.

The nuclear system references weapons which are
selected/armed through the DCU-94/A panel; the
air-to-air missile system pertains to those weapons
selected through the missile control panel; and the
multiple weapons system pertains to weapons con¬
trolled through the pedestal panel. These categories
are chosen since the electrical system and class of
weapon for each are somewhat unique, even though
their mission may be identical. For example, the
multiple weapons (pedestal panel) system can be
energized only if the nuclear system is deenergized.
Also, the air-to-air missile launch system can be
locked out if certain pedestal panel switches are en¬
ergized during FCS/missile operations. The follow¬
ing components are those which support the multiple
weapons capabilities of the aircraft.

a. Delivery mode selector panel.

b. Station and weapon selection panel.

c. Weapon delivery panel (AJB-7/WRCS integrate).

d. Weapons release computer set (WRCS) AN/
ASQ-91.

e. Lead computing optical sight system (LCOSS)
AN/ASG-26.

f. Inertial navigation set (INS) AN/ASN-63.

g. AN/APQ-120 radar set.

h. Attitude reference and bombing computer set
(ARBCS) AN/AJB-7.

The multiple weapons control system provides the
aircraft with the capability of carrying all forms of
conventional armament, which include various types
of high and low drag GP bombs, fire bombs, chemi¬
cal bombs, rockets, missiles, guns, smoke grenades,
land mines, and leaflet dispensers. The normal
weapon select and release arm functions are avail¬
able through the multiple weapons (pedestal) panel in
the forward cockpit (figure 1-43). The control stick
bomb button or trigger switch controls the applica¬
tion of weapons fire/launch voltage for all weapons
configurations. An aircraft intervalometer dispenses
the fire signals so that weapons are deployed at the
desired sequence and at the selected release inter¬
val. The aircraft emergency stores release circuit
and controls provide the jettison capability for indi¬
vidual stations or for all stations simultaneously.

DELIVERY MODE SELECTOR PANEL

The delivery mode selector panel (figure 1-43) is lo¬
cated in the front cockpit on the main instrument

panel, placarded LABS on the left, and WFN REL on
the right. The selector knob is used to select one of
twelve delivery modes. The six LABS delivery modes
are placarded DIRECT, TIMED LEVEL, TIMED
LADD, TIMED O/S, LOFT, and INST O/S. The DI¬
RECT position is used for bombing rocket or gun
firing with a fixed, depressible sight. The LOFT
position is used to perform the loft bomb ripple re¬
lease mode. The OFF position removes power from
the WRCS or the LABS bombing modes thereby pre¬
venting a release signal from reaching the bomb re¬
lease relay. The guns can be fired with the mode
selector switch in the OFF position or any other po¬
sition. The six WRCS delivery modes are on the
right side of the mode selector knob, placarded
WPN REL: TGT FIND (target finding), DIVE TOSS,
DIVE LAY (dive laydown), LAYDOWN, OFFSET
BOMB, and AGM-45. The nuclear stores jettison
button, which may be used for multiple weapons
jettison, is in the center of the mode selector knob
(refer to Jettison Controls, this section).

STATION AND WEAPON SELECT PANEL

The station and weapon select control panel (pedestal
figure 1-43) contains all switches necessary to select
and at least pre-arm the specific weapon and weapon
fire circuit. The first three controls discussed be¬
low must be energized to deploy multiple weapons
selectable on the pedestal. The remaining pedestal
controls are handled depending on the type of weapon
aboard. Also, to deploy pedestal panel weapons, a
delivery mode must be selected such as DIRECT,
OFFSET BOMB, etc. The only exception to this is
the nose gun and gun pod weapons for which the
pedestal panel controls are complete for selection
and fire. Armament bus voltage is available for air¬
craft weapon select, weapon release, and fuze arm¬
ing as soon as the landing gear handle is placed in the
UP position.

WEAPON SELECTOR KNOB

The AC positions the weapon selector for the type of
weapon aboard the aircraft; either A/G MISSILES,
GUNS, BOMBS, or RKTS & DISP. With the knob set
for the weapon aboard, voltage is available for sta¬
tion selection and for those armament station relays
which must be energized to deploy that weapon. The
control also closes circuits which govern the inter¬
valometer release pulse output mode; either SINGLE;
TRIPLE, or RIPPLE. These modes apply only to
BOMBS or RKTS & DISP weapons as figure 1-43
shows. Each of these selections are discussed in

1-106

Chang* 5

T.O. 1F-4C-34-1-1

later paragraphs. To unlock the multiple weapon
system further, the AC selects the required arma¬
ment station through the station select controls.

Note

When the weapon select knob is in the AGM-15
position, IR missile status and the audio tone
is not available until the missile arm switch
is in ARM.

STATION SELECTOR BUTTONS

The six station selector buttons are placarded LO
(left outboard), LI (left inboard), CTR (center), RI
(right inboard), and RO (right outboard), and NOSE.
(The NOSE station selector applies only to the nose
gun system.) Depressing the button(s) closes the
corresponding station select relays, which in turn
closes a portion of the weapon fire circuit. At this
point, the green (upper) light in the button housing
illuminates, which is an indication only that the but¬
ton has been depressed. The amber light illuminates
after the master arm circuits are energized. A
rheostat knob (figure 1-43) is added to the pedestal
to control the intensity of the station select green and
amber lights.

I CAUTION

The station select buttons (inboard) immedi¬
ately energize the SUU-23 gun pod prestart
circuits and start the gun inertial motor. To
avoid inertial motor burn-out avoid selecting
the stations during ground operations or any
operations not directly involving the gun pod.

MASTER ARM SWITCH

The master arm switch has two positions, SAFE and
ARM. In ARM, power is supplied to the bomb button
transfer relay and the arm nose tail switch. Appli¬
cation of power energizes the bomb button transfer
relay and the function of the bomb button is trans¬
ferred from the nuclear weapons system to the non¬
nuclear weapons system. (Refer to bomb button
transfer relay, this section.) The switch must be in
the ARM position to deliver all nonnuclear weapons,
excluding air-to-air missiles.

When master arm energized, the amber light illumi¬
nates on the activated station select button. The
amber light indications can be summarized as fol¬
lows :

1. The trigger switch and bomb button controls
are activated into the multiple weapons fire,
release, or launch circuits.

2. The aircraft is electrically configured for the
weapon selected. (The pylon-to-aircraft and
pylon-to-store adapter bundles are properly
installed.) In the case of MER/TER equipment,
the stepper switch in these units must be
properly homed.

3. For certain weapons, the light indicates that
the weapon selected is aboard.

Conditions 1 and 2 are applicable to all multiple
weapons configurations. Condition 3 applies only to
gun pods, the AGM-45 missile, the the Mark 1 Mod 0
glide bomb. These are single-carriage items only.
(With the Mark 1 Mod 0 aboard, the radar must be
operated in the applicable mode to get the amber
light.) Hence, the three controls must be positioned
to deploy any multiple weapons configuration. In the
case of gun weapons, the AC depresses the forward
trigger switch to fire. For all other pedestal weap¬
ons, a delivery mode (DIRECT, TGT FIND, etc.)
must be selected to complete the launch/release cir¬
cuit. The following controls are positioned only if a
specific weapon is aboard.

ARM NOSE TAIL SWITCH

This switch (figure 1-43, sheet 1) completes the cir¬
cuit between the master arm switch and the arming
solenoids in the aircraft ejector racks (MAU-12,
BRU-5/A, and MER/TER). The energized solenoids
retain the arming wire swivel loops and as munitions
are ejected, the arming wiref are pulled to initiate
the fuze arming sequence. In the SAFE position, the
arming wires are retained by the munition during
separation from the aircraft and the associated fuze
remains SAFE.

The arm nose tail switch also provides the selective
high/low drag capability for those weapons which
may be rigged for either a freefall or retarded drop.
In this case, the solenoids are energized to apply the
holding force for the lanyards which deploy the re¬
tardation device. (Refer to M117R and MK 82
Snakeye I bombs, and Arming Wire Routing, part 4.)

WARNING

If this switch is used to select the M117R or
MK 82 (Snakeye I) high/low drag release
option in flight, the warnings and notes listed
in Mission Description, High Drag GP Bomb
Delivery, must be carefully observed.

The switch positions and corresponding solenoids
armed are shown below.

Switch Position

Solenoid Armed

SAFE

NOSE

TAIL

NOSE & TAIL

None

Fwd and Ctr

Aft |

Fwd, Ctr, and Aft

There is no center solenoid on the MER/TER and
BRU-5/A ejector racks

With MER/TER equipment that do not have automatic
homing, the arm nose tail switch must be in the
NOSE or NOSE & TAIL position to apply power
through the sensing switch to the MER/TER stepper
solenoid. Then with a partial load of bombs aboard,
the empty stations are bypassed and the pilot re¬
leases one bomb with each pickle signal. The TAIL
position does not apply the stepping voltage and an
extra pickle must be delivered to step through each
empty MER/TER station.

Change 6

1-107

00 - 720 / 35 .

CONTROLS ANO

MOOE

STATION/& WEAPON '\SELECT

ASTERl

ROUNDS \
131 415

O REMAINING ^9

WPN REL

SAFE

RESET

,IAY

OOWM

ARM

NOSE

NOSE
& TAIL

UTILIT

STATUS

SELECTED

READY

IREADV

READY

SELECTED

.READY

BOMB RELEASE
BUTTON

(PICKLE BUTTON)

SIGHT

SHUTTER LEVER

TRIGGER

RATE SWITCH

COUNTER

GREEN LIGHT

BUTTONS

DELIVERY MODE
SELECTOR PANEL

GUNS & STORES/

SWITCH

CL TANK
ABOARD LIGHT

PEDESTAL PANEL

WEAPON
SELECT KNOB

► STATION
SELECT
LIGHT
INTENSITY

STATION JETTISON
SELECTOR KNOB

JETTISON

BUTTON

MISSILE STATUS PANEL

'v O'

mmmm

INTERVAL

ARM NOSE/TAIL i
SWITCH ;

SWITCH

Figure 1-43 (Sheet 1 of 2)

1-108

Change 6

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otoloio|Ol^)

10WANGLI

HIGH ANGLE

S »*N<M

DISTANCE

AY DOWN

f^lVE

LAVDO)

TONE ON

(^COEFFICIENT

TONE OFF
PULL UP TONE

NORM ON

NORM HOLD

NORM

control!

ACTIVATE

RESET

ihokato#
"»OT*UO»NG
STEFS UP

AURAL TONE
1 CONTROL

GYRO V"

FAST

t«CT

STEPS DOWN

• NDJCATOH
»IUSH

NO«MAl

jWARfcl

WARN

N | I UN* J UN- J UN- \ I UN* ]
IKED! lOCKEOj LOCKEt* LOCKED! |OCKEO|

STATION SELECTION

BOMB GRD
MSI HI \

MASTER

RELEASE

LOCK

E/W TARGET DISTANCE COUNTER

WEAPON RELEASE
COMPUTER CONTROL PANEL

PULL UP
TONE SWITCH

WEAPON DELIVERY
PANEL

CURSOR CONTROL PANEL

AUXILIARY ARMAMENT
CONTROL PANEL

NUCLEAR STORE
CONSENT SWITCH

BOMBIHG TIMER

OCU-94/A CONTROL MONITOR

®r

RFl/

~\£)

ARM

> I

SAFE

REL

1 l!^\

/TSv nuci '

• J, STORE
'^-'CONSENT

LJL

.. ... . 0 1

1-7- x©j

HOMWNG TIMEk

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E4E-34-1-305*2

Figure 1-43 (Sheet 2 of 2)

1-109

T.O. 1F-4C-34-1-1

With MER-10A and TER-9A equipment that have auto¬
matic homing, empty stations are bypassed regard¬
less of the arm nose tail switch position.

INTERVAL SWITCH

The interval switch is used only during BOMBS/
RIPPLE. BOMBS/TRIPLE, and RKTS & DISP/RIP -
PLE modes on the weapon selector knob, to establish
interval between each release. The switch has three
positions (0.06 SEC, 0.10 SEC, and 0.14 SEC) that
determine the pulse interval: the pulse length or
duration is always the same (23 to 33 milliseconds).
The pulse rate is measured from the start of each
pulse and therefore includes the pulse duration. The
pulse rate tolerance of the various release intervals
are: 60 to 90, 100 to 115, and 140 to 161 millisec¬
onds.

GUNS AND STORES SWITCH

This control, applicable only to gun armament, ener¬
gizes the same circuits as the GUNS position on the
weapon selector. By using this switch to select guns,
the AC is free to select other pedestal panel arma¬
ment (BOMBS, etc.) by positioning the weapon selec¬
tor. Then with the applicable stations selected and
the master arm switch closed, both the trigger and
bomb button are activated into the fire/release cir¬
cuit. Either method of selecting guns will ready all
guns for firing; this includes any gim pod aboard and
the internally mounted nose gun. One electrical dif¬
ference exists between the two methods of selecting
guns ; the GUNS position of the weapon selector limits
the optical sight operating modes to those which are
applicable only to guns. If the GUNS and STORES
switch is used, the sight operating functions are
governed by the delivery mode selector knob.

RATE SWITCH

The rate switch and the rounds counter immediately
adjacent are functional only in the nose gun weapon
system. Refer to Nose Gun System, this section.

GUNS CLEAR SWITCH

The guns clear switch is applicable only in the ex¬
ternal gun pod operating circuits. The two positions,
AUTOCLEAR and NONCLEAR, select the gun clear¬
ing mode of operation. When the autoclear mode is
used, unfired rounds are extracted from the gun and
ejected overboard at the end of each burst. When the
nonclear mode is used, the unfired rounds remain in
the gun. Hence, the NONCLEAR position is selected
when the gun pod is to be fired in short burst. When
the guns are fired in the nonclear mode and several
rounds remain unfired, a final burst must be fired
with the switch positioned to AUTOCLEAR to clear
the guns. If the gun is fired out with the gun clear
switch in the NONCLEAR position, the bolt assem¬
blies automatically clear.

REJECT SWITCH

The reject switch is applicable to the AGM-45
missile DF control circuits. Refer to the AGM-45
missile system in T.O. 1F-4C-34-1-1A.

BAND SWITCH

The band switch is intended for use with the AGM-45
missile system. The switch, however, has no func¬
tion at the present time.

FILTER SWITCH

The filter switch is functional in the filter control
network of the Mark 1 Mod 0 weapon. See T.O. 1F-
4C-34-1-1A.

Note

If the aircraft is configured with a SUU-42A/A
jumper bundle (53-09790-107) at the outboard
stations, the filter switch must be maintained
in the RED position to get release and trans¬
fer voltage to the inboard and CL stations.

1-110

Change 7

T.O. 1F-4C-34-1-1

TRIGGER SWITCH

The front cockpit trigger switch on the control stick,
is functional only in the air-to-air missile and gun
firing circuits, and in the Mark 1 Mod 0 lockon cir¬
cuit. When the spring-loaded switch is actuated,
power is supplied to initiate gun rotation and start
the ammunition feed system. The gun starts firing
when the trigger switch is depressed and ceases fir¬
ing when the trigger is released. Power can be re¬
moved from the trigger switch by pulling the gun trig
circuit breaker, No. 1 panel. The trigger switch in
the rear cockpit is always inoperative as far as weap¬
on deployment is concerned, but will supply the Mark 1
Mod 0 lockon signal. For missile launching, refer
to T.O. 1F-4C-34-1-1A.

WARNING

The trigger switch requires very little move¬
ment to initiate gun firing; therefore, the AC
should clutch the trigger only when the gun is
to be fired.

With the addition of the optical sight camera (T.O. 1F-
4E-558), the trigger becomes a double detent switch
referenced here as trigger 1 and trigger 2. The
trigger 1 position operates the camera without mu¬
nition expenditure; trigger 2 fires the selected mu¬
nition and operates the camera. Refer to Optical
Sight Camera, this part.

TRIGGER TRANSFER RELAY

a. The bomb button transfer relay can be energized
by positioning the master arm switch to ARM, and
the DCU-94/A master release lock switch AFT.

b. Guns can be selected by positioning the weapon
selector knob to GUNS, or by positioning the guns
and stores switch to GUNS & STORES, and by se¬
lecting the NOSE GUN station.

Note

*When the trigger transfer relay is energized,
all missile status lights on the missile status
panel will go out. The TK light remains on if
the tank aboard relay is energized. The tuned
status of the missiles will not be affected.

•The nose gear up limit switch must be ener¬
gized to fire the centerline gun pod. The
nose gun and the outboard guns can be fired
regardless of the nose gear up limit switch
position.

To launch air-to-air missiles, the trigger transfer
relay must be deenergized. If guns are selected, the

trigger transfer relay is deenergized by positioning
the master arm switch to SAFE.

BOMB BUTTON

The bomb or pickle button (figure 1-43) is on the
upper left side of each control stick grip in the for¬
ward and rear cockpit. The button is spring-loaded
to OFF. Depressing the bomb button (in either
cockpit) will fire/release all air-to-ground weapons
selected on the multiple weapons control panel
(except guns), or on the DCU-94/A monitor-control
panel. Power can be removed from the bomb release
button by pulling the A/G weapon release cont cir¬
cuit breaker, No. 1 panel.

BOMB BUTTON TRANSFER RELAY

The bomb button transfer relay must be energized to
pull the bomb button into the multiple weapons re¬
lease circuits. The relay is energized when the
master arm switch is positioned to ARM, providing
one of the following switches is positioned AFT or
SAFE:

a. DCU-94/A all station selector switches - AFT

b. DCU-94/A master release lock switch - AFT

c. Nuclear store consent switch - SAFE

PULLUP LIGHT

The pullup light on the front cockpit instrument panel
is a press-to-test typje light. The lamp intensity can
be controlled by rotating the outer ring to vary the
size of the iris over the lamp. The pullup light illu¬
minates during all release modes when the bomb
button signal is generated, and goes out when the
bomb button is released.

PULLUP TONE

An audio tone is present in the headset for specific
AN/AJB-7 and WRCS automatic modes (except AGM-
45). With the bomb button depressed, the tone func¬
tions until a bomb release signal is generated. The
tone is generated by the AN/AJB-7 audio tone gener¬
ator and the volume level is controlled by the aural
tone control on the left console.

Pullup Tone Cut-Off Switch

The pullup tone cut-off switch is on the left console,
rear cockpit. The switch enables the aircrew to
preclude external transmission of the audio tone
during any bombing mode in which the tone signal is
involved. With the switch in TONE ON, the audio
tone signal is transmitted through the UHF transmit¬
ter. The TONE OFF position deenergizes the same
tone transmit circuit. In either case, the aircrew
hears the tone and all tone functions remain the same. I

Change 7

1-111

T.O. 1F-4C-34-1-1

WEAPON RELEASE/LAUNCH MODES

The following generally describes the methods by
which the aircrew may deploy bomb and rocket or
dispenser armament. (AGM weapons and gun sys¬
tems are described later in this section.) It is
assumed that the AC has selected the weapon, se¬
lected the applicable station(s) energized master
arm, and selected the DIRECT delivery mode. The
following release options are those which correspond
to the selectable positions on the pedestal weapon
selector (figure 1-43).

BOMBS/SINGLE

When the weapon selector knob is positioned to
BOMBS/SINGLE, one bomb is released from each
station selected when the bomb button is depressed
(figure 1-44). If five stations are selected and loaded,
five bombs are released simultaneously. This applies
to either single or MER/TER bomb carriage con¬
figurations. In the case of singles carriage, the
station amber light goes out as each weapon leaves
the pylon. Considering multiple carriage, the amber
light goes off as each MER/TER carrier becomes
completely empty.

BOMBS/TRIPLE

With BOMBS/TRIPLE selected and the bomb button
held depressed, three bombs are ripple released
(figure 1-44). The time interval between bombs is
established by the position of the interval switch;

0.06 sec, 0.10 sec, or 0.14 sec. The bomb release
button must be held depressed until the three bombs
are released. With only one station selected, three
bombs are released from that station (assuming
MER/TER carriage). When a left and a right station
is selected, the release pulse is directed alternately
between the left and right station, releasing two
bombs from one side and one bomb from the other.
There is no provision for determining which side
receives the first release signal. With all stations
selected, bombs will triple-release with each bomb
button signal until the entire weapon load is expended.
The station amber light functions as described above.

BOMBS/RIPPLE

With BOMBS /RIPPLE selected and the bomb button
held depressed, the selected bombs are released
singularly with the time interval between bombs
established by the position of the interval switch
(figure 1-44). Bombs continue to be released until
the bomb button is released, or until the selected
station load is depleted. When five stations are se¬
lected, all bombs from the outboard stations are
released, then the inboard stations, and finally the
centerline station. The release pulse is directed
alternately from left to right wing stations. There
is no provision for determining which side (left or
right wing station) receives the first release pulse;
normally the left side receives the first release
pulse. (If the pilot selects both stations on one
wing, i.e., LO and LI, then weapons release alter¬
nately from each of the stations.) The station amber
light goes off as each pylon station becomes empty
(singles), or as each MER/TER becomes completely
empty.

ROCKETS AND DISPENSER/SINGLE

Selecting RKTS & DISP and depressing the bomb

button will fire-out one rocket pod, or fire out one

shot consisting of a predetermined number of tubes
from one CBU dispenser. If five stations are se¬
lected, five rocket launchers or CBU's will fire
simultaneously with the application of each bomb
button signal. Only the DIRECT delivery mode can
be used to fire rocket launchers or CBU dispensers.

In the case of CBU's, the station amber light flashes
when any CBU on that station has two shots remain¬
ing (which may consist of several tubes). The light
goes out when all CBU’s are empty. With rocket pods
aboard, the amber light will not provide the expended
indication; the light remains on when the pods are
empty. With either armament aboard, the AC can
select BOMBS and release the empty pods/dispensers
and observe the station amber light go off as a re¬
lease indicator.

Note

TER 9A and MER 10A equipment does not have
the CBU flasher circuit as stated above.

ROCKETS AND DISPENSER/RIPPLE
Note

The single firing pulse in the ripple mode is
not of sufficient duration to completely fire-
out the entire rocket launcher. The remain¬
ing rockets will fire, however, as the pulse
steps back through the partially expended
launchers.

With RKTS & DISP/RIPPLE selected and the bomb
button held depressed, the CBU dispenser (or rocket
launcher) will fire singularly at a time interval be¬
tween each dispenser established by the position of
the interval switch, either 0.06 sec, 0.10 sec, or
0.14 sec. Ripple firing pulses continue until the bomb
button is released or until the selected aircraft sta¬
tion fires out completely. The firing pulses are
directed alternately (and symmetrically) between the
left and right wing stations. When five stations are
selected, only the outboard station armament is
initially fired out. The firing pulses will not transfer
to the inboard stations until the outboard stations
are de-selected; nor will the firing pulse reach the
centerline station until both the outboard and the
inboard station selector buttons are pushed OFF.
There is no provision for determining which station
(left or right) receives the first firing pulse. The
station amber light functions previously stated
apply here.

GUNS

The gun pods (SUU-16/A or SUU-23/A) and the
M61A1 nose gun are selected for firing as stated
previously. The AC selects GUNS, depresses the
appropriate station selector(s), and energizes mas¬
ter arm. The corresponding station amber light
illuminates and the trigger circuit is hot. These gun
systems are described later in this section.

A/G MISSILES

The AGM-45, AGM-12B and C, and the Mark 1 ModO
air-to-ground weapon are each initially selected as
stated previously. The weapon is selected, the appli¬
cable station(s) are selected, and the master arm
circuits are energized. Additional controls which
are unique in these missile control circuits are
discussed later in this section.

1-112

Change 5

T.O. 1F-4C-34-1-1

SINGLE

Each bomb button signal simultaneously
releases one bomb from each selected
station.

When two or more stations are selected,
there is no indication which station
receives the first release pulse, left or
right. Normally, the left station
receives the first release pulse.

Holding the bomb button depressed releases
bombs continuously in the left-right order
and at the selected bomb release interval.

TRIPLE

Holding the bomb button
depressed releases three bombs
in the ripple release sequence
and at the selected bomb
release interval.

1 RELEASE PULSE

24 RELEASE PULSE

3 RELEASE PULSES

The MER and TER release
sequence always remains as
illustrated here. Empty
points are automatically
stepped over.

T.O. 1F-4C-34-1-1

AIRCRAFT WEAPON SYSTEM CONTROLS |F-4E) AFTER T.O. 1F-4E-556

This description contains information pertaining to
the installation of an improved conventional weapons
control system in all F-4E aircraft. The major
changes and improvements may be generally de¬
fined as follows:

a. The forward cockpit weapons control panels are
relocated so that all weapons functions and indica¬
tions are controlled and observed in one common
area.

b. The weapons select functions and switching logic
is designed so that the AC may switch from any
weapons mission status into a close-in, air-to-air
environment with rapid, finger-tip control action.

c. External store jettison functions are simplified
and occur through controls on the weapons panels.

In fact, anything to do with selective conventional
stores separation occurs through these same panels.
Fuel tank and ECM jettison controls previously lo¬
cated on the forward cockpit left console are deleted.
The missile jettison capability is removed from the
external stores emergency release button.

The major control panel changes and additions occur
in the front cockpit as shown in figure 1-44A; the
rear cockpit modification is shown in figure 1-44B.
Items that are added to the front cockpit are the
throttle weapons controls, the Aircraft Weapons Re¬
lease Unit (AWRU), and the head-up weapon select
and arm display lights mounted on the left under the
glare shield.

All air-to-air and air-to-ground weapons are armed,
released, and jettisoned through these controls.

There is essentially no interlock between trigger-
fired and bomb button-released weapons. In other
words, air-to-air weapons fired through the trigger,
and bomb/dispenser munitions released by the bomb
button may be armed for launch simultaneously. If
the aircraft is loaded with both air-to-air and air-
to-ground weapons that are launched through the
trigger, a rapid method exists for switching the
trigger circuit to accomodate either of the two. With
the launch circuits so arranged, aircrews on air-to-
ground missions can instantly meet air-to-air com¬
mitments. The aircraft weapon release systems
(WRCS, AJB-7, etc) are not changed.

AIR-TO-GROUND WEAPONS

DELIVERY MODE SELECTOR

The functions of this control remain unchanged. One
of the delivery modes must be selected in order to
release any air-to-ground weapon available on the
weapon selector (WPN SEL) knob. The DIRECT mode
applies an immediate release signal. The remaining
selections are the (T) timed, AN-AJB-7, and WRCS
automatic release systems. The OFF and TGT FIND
positions of this control are essentially the SAFE
positions for the munitions available on the WPN
SEL knob. This is true since the master arm switch

is a common ARM/SAFE switch for all conventional
weapons and must be ARMED for heat and radar
missiles.

WEAPON SELECTOR KNOB

The AC positions the weapon selector for the type of
munition aboard. The control essentially provides
the same electrical functions as the previous control,
but the selective positions are changed. The BOMBS
and RKTS & DISP positions select those munitions
respectively and apply operate power to the Aircraft
Weapons Release Unit (AWRU). These are the only
WPN SEL positions that operate the AWRU. The
ARM position selects Anti-Radiation Missiles and is
applicable to the AGM-45 missile or any other mu¬
nition of this type which may become available. The
TV position is selected for the TV guided weapons or
any EO weapon requiring a video display. The AGM-
12 position is described in a separate part of this
manual.

Note

• The AGM-12 control handle (left console) is
not installed in some aircraft, and therefore
removes the weapon capability. Although
aircraft (71-237) and up contain the control
handle for AGM-65 (Maverick) missile oper¬
ations, the AGM-12 capability is not avail¬
able in these aircraft.

• The ARM and TV positions control the trig¬
ger circuits so that guns, radar and heat
missiles cannot be fired unless the CAGE
signal is present. (Refer to the CAGE des¬
cription in later paragraphs.)

The remaining selections on this control are A, B,
and C. The C position is an open position and has no
current use. The B position provides the same
switching function as the AIR-TO-AIR button in the
rear cockpit. The B selection reverses (uncages) the
cage signal applied to weapon system components
through the CAGE button on the throttle. The cage
and uncage functions are described in later para¬
graphs.

Note

The B position, and currently the C position
are OFF/SAFE selections on the WPN SEL
control.

The WPN SEL A position applies continuous (non¬
pulse) voltage to the selected station(s) as long as
the bomb button is depressed. The position may be
used for munitions which contain their own interva-
lometers such as CBUs, rocket packages, or multi¬
ple spray containers that are dispensed simulta¬
neously. With A selected, only these munitions can
be launched from MER/TER equipment; bomb mu¬
nitions will not release. With the bomb button sig¬
nal applied, one dispenser fires completely from
each selected station. The bomb button is released

1-114

Change 8

NOSE

maii

i io j u «* |

I ARM [ ARM ARM | ARM j j

0«*fCT

AUTO

R cw on

t ABS/WPN REL

QTY-|

INTRVL

P Xio

ARM

T®

V NORM \ ^

STORES

iot/msi

CttM

CUA*

MASTER

SWITCH

WEAPON

SCOPE DISPLAY
BUTTONS

HEADS-UP
DISPLAY LIGHTS

QUANTITY

- CAGE
BUTTON

BUTTON » 1

» i-i 1 —. TRIGGER
;4 1> (DOUBLE
iO;'/’; DETENT)

NOSE GEAR STEERING

-ARR

BUTTON

CONTROL STICK

MULTIPLE WEAPONS
CONTROLS

SELECTIVE

JETTISON

GUNS/MISSILE SWITCH
UP-HEAT REJ.
CTR-HEAT
FWD-RADAR ^
AFT-GUNS — 7 !

dsk|!

OFF |

AFTER T.O. 1F-4E-556

STATION SELECT
BUTTONS

(SELECT & ARM LIGHTS)

T.O. 1F-4C-34-1-1

MISSILE

STATUS

LIGHTS

TANK ABOARD
GHT

DELIVERY

MODE

SELECT

AIRCRAFT
WEAPONS RELEASE
UNIT

FRONT COCKPIT

M I H

E ! E

RDR

■?

t ;

RDR

RDR ]

PEDESTAL PANEL
ASSEMBLY

THE CENTER STA. WING STA., AND ECM JETTISON

SWITCHES ON LEFT CONSOLE ARE REMOVED BY T.O. 1F-4E-556.

AUTO ACQUISITION FUNCTION ADDED. HEADING
HOLD FUNCTION REMOVED.

AFTER T.O. 1F-4E-558.

F-4E (71-237) AND UP.

4C-34-1 -1 -(211)

Figure 1-44A

1-114A

Change 7

THROTTLE

ASSEMBLY

AUTOPILOT

DISENGAGE

T.O. 1F-4C-34-1-1

CONTROLS & INDICATORS J_

- |F-4E

REAR COCKPIT

Figure 1-44B

and depressed again to fire the next set of dispens¬
ers. This is essentially a manual-salvo firing se¬
quence since the mode is comparable to the SALVO
mode shown in figure 1-44C. The A method is non¬
automatic since the AWRU is bypassed; the MER/
TER stepping sequence is accomplished by releas¬
ing the bomb button.

STATION SELECT BUTTONS

The station select buttons (figure 1-44B) must be
depressed to select and fire any air-to-ground con¬
ventional weapon, including gun pods and the nose
gun. The station select green lights illuminate as
soon as the buttons are depressed. The amber ARM
lights are fire-ready lights and illuminate to indicate
a fire-ready bomb button or trigger circuit. A rheo¬
stat knob is provided next to the GUN station button
to control the station lights intensity. The station
select buttons also provide the selective jettison
function for the four wing stations and the CL station
(stations 1, 2, 5, 8 and 9). With the exception of
heat missiles, the required station button(s) must be
depressed to jettision any munition (or fuel tank) plus
suspension equipment from the corresponding air¬
craft station. (Refer to Jettison Controls, this part.)

In order to obtain the fire-ready (station ARM light
on) indication, the following control conditions must
exist.

a. The delivery mode switch is not in the OFF or
TGT FIND position (nose gun station excluded).

b. The weapon is selected (on WPN SEL knob, or
guns on guns/missile switch) and the weapon aboard

is essentially compatible with the weapon selected.
For the nose gun, rounds are available and the rounds
limiter is not activated.

c. The station(s) are selected.

d. With the WPN SEL in BOMBS, the arm nose tail
switch must be in one of the armed positions to get
the station ARM light, and therefore get an armed
bomb release. (See Arm Nose Tail Switch.)

e. Master arm is in ARM.

MASTER ARM SWITCH

The master arm switch is a lock-toggle switch with
the lock detent in the SAFE position. In these air¬
craft, the switch performs a true MASTER ARM
function for all conventional weapons. The ARM po¬
sition must be selected to fire guns, heat and radar
missiles, and launch munitions selected through the
WPN SEL knob. Hence, the air-to-air weapons can
be armed for launch simultaneously with the air-to-
ground munitions, provided the two are not launched
through the same (trigger) control. With ARM se¬
lected, the ARM light on the heads-up display illumi¬
nates (amber). The ARM light illuminates any time
the master arm switch is energized, no other control
activity is necessary. The ARM light therefore, is
not a fire ready indicator; it simply announces the
position of the master arm switch. If the remaining
weapons controls are also energized, then the station
ARM lights together with the heads-up ARM light,
provide the fire ready indication.

Note

With bombs selected, the station ARM (am¬
ber) light will not illuminate unless the arm
nose tail switch is in one of the armed (ON)
positions.

For air-to-air missiles and the nose gun, the fire-
ready indication is provided by the illumination of
both the heads-up ARM, and any one of the GUN,
HEAT, or RADAR lights for those munitions respec¬
tively. For the nose gun, the station (amber) ARM
light is also on.

Note

With master ARM energized and with heat
selected on the guns/missile switch, AIM-
40 cool-start is initiated immediately.

ARM NOSE TAIL SWITCH

This control provides all of the same functions as
described previously. The important difference is
that the switch closes a fuze select-ready relay in
the BOMBS/station ARM light circuit. With the
weapon selector in BOMBS, the station ARM light
will not illuminate unless the arm nose tail switch
is energized. Conversely, the SAFE position of the
switch does not inhibit the BOMBS release circuit.
Bombs will release (SAFE) if all other release con¬
trols are energized and with only the station green
light(s) on. Therefore, the AC will notice that with

1-114B

Change 6

T.O. 1F-4C-34-1-1

BOMBS selected and station green light(s) on, an
ARM-light-off indication does not necessarily mean
that the bomb button circuit is in a SAFE condition.

If the BOMBS position is used to bomb-off rocket or
CBU dispensers in a jettison situation, then the arm
nose tail switch should be in one of the (ON) positions
to get the proper station ARM light indications (MER/
TER stations empty).

AIRCRAFT WEAPONS RELEASE
UNIT (AWRU)

The AWRU is added to the forward cockpit as shown
in figure 1-44A. The unit receives operate power
only by the selection of BOMBS or RKTS andDISP
modes on the weapon selector. The control panel
contains two INTERVL controls, and a quantity (QTY)
selector. The interval controls provide the time in¬
terval (in seconds) between each weapon release,
and therefore determines bomb spread and pattern
length. The rotary control provides selectable in¬

tervals between 0.05 to 1.0 second, provided the
INTRVL rate switch is in the NORM position. With
the XI0 factor selected, the intervals range from
0.5 to 10 seconds.

The AWRU operates in either one of two modes;
manual or automatic. In manual, the unit develops
its output coincident with each pickle signal, and the
pickle signal must be interrupted and reapplied to
get each subsequent output. In automatic, the unit
develops pulsed outputs and the bomb button must be
held depressed to continue the pulse train. The
INTERVL setting applies only to the automatic mode
and is simply the time duration between the start of
a pulse, and the start of the next pulse. The length
of time the pulse is ON is 62.5% of the selected
NORM interval, and 60% of a X10 interval.

The QTY control selects the singles, pairs, and
salvo release sequences, and can be set to yield an
exact number of output pulses. The QTY control
selections and the sequences obtained may be defined
by the following. (Refer to figure 1-44C.)

Change 9

1-114 B 1/(1-114 B2 blank)

AWRU OPERATION WITH MER/TER

Single-Manual

T.O. 1F-4C-34-1-1

The QTY position 1 selects a single, AWRU manual
release sequence. One weapon is released each time
the bomb button is depressed. With multiple stations
selected, release occurs in alternate left-right order
with the first release signal delivered to the left se¬
lected station. The release signal is continuous un¬
til the bomb button is released.

Single-Ripple

The single-ripple sequence is obtained by selecting
any one of the QTY numerical positions 2 thru 18.
With the release signal held, the total weapons re¬
leased is equal to the QTY setting; then the release
signal is automatically interrupted. The interval be¬
tween each release pulse is governed by the INTRVL
controls. At the completion of the set number of re¬
leases, the bomb button may be released and rede¬
pressed to initiate the sequence again. With multiple
stations selected, release is in left-right order.

The release signal for the last weapon is retained
until the bomb button is released.

Single-Continuous

This mode is the same as single-ripple, except the
quantity of weapons released is not automatically
limited by the AWRU. With QTY position C selected
and the pickle signal held-in, weapons release in
left-right order until the stations empty or the pickle
signal is terminated. The time between each weapon
is governed by the INTERVL controls.

Pairs-Manual

The QTY position P is selected to get the pairs mode.
One set of simultaneous left and right release pulses
is generated each time the bomb button signal is ap¬
plied. Therefore, with any two (or more) stations
selected, two weapons are deployed simultaneously
with each pickle signal. With one station selected, the
system is essentially in a single-manual mode.

Salvo

The salvo mode is obtained by selecting S on the QTY
knob. With the bomb button signal held, continuous
release pulses are applied to each selected station;
the interval between each release pulse is set by the
INTRVL controls. Hence, with five stations selected,
five weapons salvo followed by another five at the set
interval. With two stations selected, the system is
essentially in a pairs-ripple mode.

AWRU OPERATION WITH MAU-12
(SINGLE CARRIAGE)

When weapons are single-carried on the MAU-12
armament pylons, the aircrew can encounter a situ¬
ation that would result in a release of more weapons
than anticipated.

WARNING

For MAU-12 single carriage, the AWRU re¬
lease interval and quantity selector should
be considered unreliable when more than one
station is selected.

To explain the preceding statements, consider the
following station transfer differences in aircraft with
MER/TER stores aboard, and aircraft with single
stores aboard. (Assume that at least two aircraft
stations are selected.)

a. With MER/TER carriers, QTY 1 selected:

The firing function is transfered to the next station
only after termination of the first release pulse by
releasing the bomb button.

b. With single carriage, QTY 1 selected: The fir¬
ing function is transferred to the next station when
the bomb-gone switch on the MAU-12 rack extends.
This may occur before the bomb button signal is re¬
leased.

When considering item (b), if more than one station
is selected, the release function transfers from the
first station to a second station by merely releasing
the first store. With the bomb button held during
transfer, the weapon on the second station releases,
even though QTY 1 is selected. The weapons would
release at a rate equal to how fast the bomb-gone
switch activates. With P (pairs) selected, the same
considerations apply except that four weapons would
release instead of two (assuming four stations are
loaded and selected). Finally, if a ripple mode is
selected (QTY 2 or more or C) the release interval
between bombs cannot be accurately acquired.

The situation can be avoided entirely for the QTY 1
or P (pairs) mode by selecting only that station (or
those stations) to be released.

AIR-TO-AIR WEAPONS

The reference air-to-air weapons in this discussion
implies weapons which have select-ready indicators
on the heads-up display (figure 1-44A). These mu¬
nitions are selected by the guns/missile switch on
the left throttle. (Gun pods are also selected by this
control, but the gun pod select-ready indication is
received on the corresponding station select buttons.)
The guns/missile switch is actually a weapon select
control used to enable the nose gun and the heat and
radar missile launch systems. Since the master
arm switch performs the ARM function for both the
guns/missile switch and the WPN SEL control, then
the trigger switch and bomb button circuits can be
activated for weapons deployment simultaneously.
This was stated previously, but the point to be made
is that air-to-air munitions can be maintained es-
esentially in a launch-ready state during any other
type of mission, including air-to-ground operations.
The following description demonstrates the switching
function.

Change 9

1-114C

■ NORMAL RELEASE SEQUENCE

5 STATIONS LOADED, 5 STATIONS SELECTED, BOMBS OR RKTS DISP. MUNITIONS

SINGLES

SINGLE-MANUAL (qty position l)
ONE WEAPON IS RELEASED WITH EACH BOMB
BUTTON SIGNAL IN ALTERNATE (LEFT/RIGHT)
ORDER.

SINGLE-RIPPLE (qty position 2 thru 18)
WITH BOMB BUTTON SIGNAL HELD, WEAPONS
RELEASE ALTERNATELY AT THE SELECTED
RELEASE INTRVL ; THE TOTAL WEAPONS
RELEASED IS EQUAL TO THE QTY SETTING.

SINGLE-CONTINUOUS (qty position c)
WITH THE BOMB BUTTON SIGNAL HELD, WEAPONS
RELEASE ALTERNATELY AT THE SELECTED RE¬
LEASE INTRVL UNTIL THE STATIONS EMPTY OR
THE BOMB BUTTON SIGNAL IS TERMINATED.

WITH TWO OR MORE STATIONS SELECTED
IN SINGLES MODE, THERE IS NO INDICA -
TION WHICH STATION RECEIVES THE
FIRST RELEASE PULSE, LEFT OR RIGHT.
NORMALLY, THE LEFT STATION
RECEIVES THE FIRST RELEASE PULSE.

PAIRS

PAIRS-MANUAL (QTY position p)

TWO WEAPONS ARE RELEASED SIMULTANEOUSLY
(FROM DIFFERENT STATIONS) EACH TIME THE
BOMB BUTTON IS DEPRESSED. AT LEAST TWO
(ANY TWO) STATIONS MUST BE SELECTED.

Figure 1-44C (Sheet 1 ol 2)

1-114D

T.O. 1F-4C-34-1-1

NORMAL RELEASE SEQUENCE (continued)

}F-4E ,

5 STATIONS LOADED, 5 STATIONS SELECTED, BOMBS OR RKTS/DISP. MUNITIONS

AFTER T.O. 1F-4E-556

SALVO (OTY POSITION S)

WITH BOMB BUTTON SIGNAL HELD, ONE WEAPON
IS RELEASED SIMULTANEOUSLY FROM EACH SELECTED
STATION; THE INTERVAL BETWEEN EACH SALVO
RELEASE IS EQUAL TO THE INTRVL SETTING

ES53U

REFER TO T.O. 1F-4C-I FOR DETAILED
INFORMATION CONCERNING THE MINIMUM ALLOWABLE
RELEASE INTERVALS THAT MAY BE USED WITH
THE AWRU SALVO MODE.

MANUAL-SALVO (WPN sel position a)

WITH RKTS OR DISP ABOARD, ONE WEAPON
IS FIRED FROM EACH SELECTED STATION WITH
EACH BOMB BUTTON SIGNAL.

(THE AWRU IS BYPASSED).

THE MER AND TER RELEASE SEQUENCE ALWAYS
REMAINS AS ILLUSTRATED HERE. EMPTY POINTS
ARE AUTOMATICALLY STEPPED OVER.

Figure 1-44C (Sheet 2 of 2)

4C-34-1-1-(212-2)

Chang* 7

1-114E

T.O. 1F-4C-34-1-1

GUNS/MISSILE WEAPON SELECT

The guns/missile switch is a four position control
which performs the weapon select function for guns,
radar and heat missiles, and performs station se¬
lect functions for the heat missiles. The positions
are arranged as follows:

Forward - Radar Missiles
Center - Heat missiles
Rear - Guns

Up - Heat Reject (spring loaded)

There is no OFF position on the control. With mas¬
ter arm SAFE, one of the head-up lights illuminate
simply to indicate the existing position of the guns/
missile switch, either the HEAT, GUNS, or RADAR
light. The A/C can cycle the guns/missile switch
through the three positions and watch the three head-
up weapon select lights illuminate. (This assumes the
landing gear handle is up, or the armament safety over -
ride is depressed, and that the weapon selector is
not in the TV or ARM positions.) Therefore, when
the landing gear handle is raised, one of the lights
will indicate the present guns/missile switch posi¬
tion. If at this point, the master arm switch is
placed to ARM (with no further munition preparations)
the head-up select light goes off and the ARM light
comes on. This simply means that the master ARM
signal is present, and that further weapon prepara¬
tions are necessary. Hence, a complete nose gun or
missile weapon ready indication is the illumination
of both the head-up ARM light and the applicable
weapon head-up light. (This does not include gun
pods.)

GUNS STATION SELECT AND ARM

The nose gun station select circuits are essentially
unchanged. With the guns/missile switch in guns
(heads-up GUN light on), the nose gun station button
is depressed to remove an interlock in the master
arm circuit; the station green light illuminates. The
master arm switch is placed to ARM to energize the
remaining gun ready relays and enable the trigger
switch circuit. Now the station ARM, and the heads-
up ARM lights illuminate, along with the head-up
GUN light which was already on. In this particular
case, the GUN and ARM head-up lights, and the gun
station amber light all provide the weapon ready
indication. The ready indication cannot occur unless
rounds are aboard and not limited, and the WPN SEL
control is placed in some position other than TV or
ARM. The TV and ARM positions completely lock¬
out the trigger switch/gun circuits so that gun-ready
cannot be obtained. (See Cage Functions, this part.)

Note

The TV and ARM weapon selections lock out
the gun, radar and heat missile fire circuits
(and the respective head-up lights) unless the
CAGE signal is present.

If gun pods are aboard, the head-up GUN light has no

function. Only the head-up ARM light and the station

ARM light provide the fire ready indication.

MISSILE STATION SELECT AND ARM

Refer to T.O. 1F-4C-34-1-1A for heat and radar
missile descriptive data.

CAGE FUNCTIONS

The momentary, push button cage control is added to
the inboard throttle assembly (figure 1-44A) and the
AC can immediately apply the CAGE signal with min¬
imal hand motion. The optical sight electrical cage
function is removed from the control stick ARR but¬
ton and relocated to the cage button. The basic pur¬
pose of the control is to rapidly switch the aircraft
systems into an air-to-air operational status. De¬
pending on the present status of the aircraft, the
cage signal effects any one or all three of the follow¬
ing aircraft systems: the air-to-ground weapons
release system, the optical sight system, and the
radar system. The cage signal, as it effects these
systems, may be defined by the following.

a. If the WPN SEL control is in ARM or TV, the
cage signal switches the trigger into the launch cir¬
cuit of whatever munition is selected by the guns/
missile switch.

b. The LCOSS switches and locks-up in an air-to-
air mode (if A/G was previously selected). Further
operation of the sight is a function of the guns/missile
switch position, and whether or not radar lockon
exists.

c. With AN/APQ-120 radar power switch in any
position but OFF or TEST, the cage command
switches the radar into BST (transmitter ON) mode,
with R1 auto-acquisition available in both cockpits.

The AIR-TO-AIR light (figure 1-44B) comes on.

Notice that if WPN SEL is not in TV or ARM, then
the cage command has no meaning as far as pre¬
ceding step a is concerned. If the sight is already
operating in the air-to-air lead compute mode (step b),
the cage command does nothing more than apply the
reticle stiffness (1000 ft lead compute) signal, illus¬
trated in figure 1-50. Finally, if the radar is being
operated under the conditions of step c with lockon,
then CAGE has no radar function.

Note

The AC can inadvertently break lockon by de¬
pressing the CAGE button (with the intention
of obtaining sight stiffening) if the WSO is
locked on in the RDR mode. Depressing the
CAGE button does not break lockon if the
WSO is locked on in the BST mode and in the
5-mile range.

In order to demonstrate the system, consider an ex¬
ample of the cage function. Suppose the aircrew is
engaged in a Mark 1 Mod 0 (Walleye) mission. The
appropriate operating modes (TV) are selected in
both cockpits and the optical sight is in AG with the
required reticle depression setting. Hence, the AC
has energized DIRECT, weapon station, TV weapon
select, and master ARM; before (71-237) the WSO
has radar mode TV selected. The trigger and bomb
button is ready in the weapon lockon/release network.

1-114F

Change 7

T.O. 1F-4C-34-1-1

Note

In aircraft 71-237 and up, the TV position on
the radar panel is functional only for radar
BIT operations. The radar may be in any op¬
erating mode (or OFF) during the launch of
TV guided weapons.

At this point, the head-up ARM light and station
ARM light is on. The AC may set up the nose gun
and observe heat missile status functions by accom¬
plishing the following.

1. Energize nose gun station; the station green
light comes on. Select the desired gun rate
(Hi/Lo).

2. If heat missiles are aboard, a missile status
HEAT light is on indicating the current selected
station. The HEAT status light for the selected
station remains on continuously regardless of
the guns/missile switch position.

Note

With master ARM energized (as in this ex¬
ample), selecting heat on the guns/missile
switch energizes AIM-4 cool start. Once
initiated, cooling cannot be reversed.

3. Prior to aircraft (71-237), radar missiles can¬
not be tuned, nor will they maintain a tuned
status with radar mode TV selected. The RDR
MSL power switch may be maintained in STBY
in order to have continuous missile warm-up
voltage.

In aircraft (71-237) and up, the TV position of
the radar mode knob has no weapon or video
display function. The AC may select CW ON
and tune missiles any time during air-to-
ground mission (and prior to the CAGE signal),
or maintain the CW STBY position as required.

Cage, Guns Selected

In this example, what occurs with the application of
the CAGE signal is evident by applying the definitions
of steps a, b, and c stated previously. Therefore
with guns selected on the guns/missile switch, the
CAGE signal places the trigger in the nose gun net¬
work and the LCOSS switches into the 1000 ft. lead
compute operating mode. If lockon occurs, the op¬
tical sight provides lead compute at radar range.

The head-up GUN light, ARM light, and gun station
ARM light are illuminated and the nose gun is ready
to fire. In the rear cockpit, the AIR-TO-AIR light
illuminates with the application of CAGE.

Cage, Heat Selected

If heat missiles are selected on the guns/missile
switch, the missile/trigger network is energized
and the missile tone circuits are enabled. The op¬
tical sight cages at RBL. With AIM-9's aboard, the
head-up HEAT light is on immediately. With AIM-
4D's aboard, the HEAT light illuminates indicating
a cooled missile. Also, the seeker uncage functions
of the ARR button are available. With the missile

tone signal, the AC can fire. Refer to T.O. 1F-4C-
34-1-1A.

Note

The AN/APQ-120 computer will compute
AIM-4D launch equations with heat or guns
selected and AIM-7 equations with radar
selected.

Cage, Radar Selected

Considering radar missiles at CAGE, missile tuning
begins when CW ON is selected. (In aircraft 71-237
and up, tuning may be accomplished prior to CAGE.)
The four radar (RDR) status lights illuminate as soon
as their corresponding missiles tune. (Missile tuning
is independent of the guns/missile switch position or
master arm.) With the guns/missile switch in radar
and one or more missiles tuned, the head-up RADAR
light comes on. The AC may select Interlocks IN or
OUT and proceed with the respective launch proce¬
dure. With the CL TK aboard light on, only the two
aft missiles can be launched. At CAGE, the sight
reticle locates at RBL and the AIR-TO-AIR light in
the rear cockpit illuminates.

Cage, Scope Displays (Aircraft 71-237 and Up)

With the addition of the MSDG and TISEO systems,
the crew may independently select either the TISEO
TV, weapon TV, or the radar video on the front and
rear scope indicators. (The display select controls
for the AC are shown in figure 1-44A). With a TV
display in progress, the CAGE signal immediately
switches the forward indicator into the radar display,
but the rear indicator display remains as selected by
the WSO.

CAGE RESET

The cage reset capability is available in both cock¬
pits. In the forward cockpit, the cage reset signal
is applied by momentarily selecting the B position
of the WPN SEL control. In the rear cockpit, the
WSO may depress the AIR-TO-AIR button (figure
1-44B). In either case, the AIR-TO-AIR light goes
out. The cage reset function simply returns the air¬
craft to the status attained prior to the application of
the CAGE signal. In the example previously stated,
the weapons launch, LCOSS, and radar operate modes
would return to the TV weapon functions. If the AC
leaves the WPN SEL in B position, this will not in¬
hibit the radar or LCOSS cage functions, or future
cage reset functions of the AIR-TO-AIR button.

AIR-TO-GROUND MISSION, TRIGGER INTERLOCKS

To further demonstrate the system, consider the
situation when the mission involves the use of
BOMBS or RKTS and DISP munitions deployed
through the bomb button. With master arm ener¬
gized, the trigger switch is HOT in the air-to-air
weapon launch circuit selected on the guns/missile
switch. With GUNS selected for example, the only
way to SAFE the nose gun is to de-select the nose

Change 8

1-114G

WEAPONS RELEASE COMPUTER SET

DIRECT

//-THTFIND^^
^^s-DIVE TOSS
DIVE 4

o\B LAY

"down

/JHP^offset

OFF-0

DISTANCE

j t» o *>■ -

RESET

INSERT

QCOW

OPTICAL SIGHT

STEERING

-—SLANT RANGE FROM AN APQ-120

-ROLL AND

STABILIZATION
SIGNALS
FROM INS

DELIVERY MODE
SELECTOR PANEL

AND RANGE

STEERING

AGM-45 MISSILE

BOMB RELEASE
BUTTON —

BALLISTIC
COMPUTER
(WRCS COMPUTER)

OPERATE
POWER &
INERTIAL
SIGNALS

STEERING
AND RANGE

AIR-TO-GROUND

RANGE

RADAR

AN/APQ-120

WEAPON

RELEASE

NETWORK

SIGNAL

AGM-45

MANEUVER

COMMANDS

LEVEL

COMPUTER CONTROL PANEL
(WRCS PANEL)

CURSOR CONTROL PANEL

TGT

INS

PICKLE

SIGNALS

Figure 1-45

1-114H

Change 5

T.O. 1F-4C-34-1-1

gun station. If HEAT missiles are aboard and with
HEAT selected (AIM-4D cooled), there is no way to
SAFE the trigger circuit except to de-select the
HEAT position. With radar missiles selected and
tuned (CW ON), the only way to prevent the immedi¬
ate trigger-launch of radar missiles is to select in¬
terlocks IN. Therefore, when all three air-to-air
munitions are aboard with master arm energized,
the trigger can be rendered SAFE by selecting the
gun weapon on the throttle and by maintaining the
gun station selector deenergized.

There is one situation which the AC must consider
during combat conditions. If it becomes necessary
to rapidly switch from one air-to-air weapon to
another - say from radar to guns - the AC must not
become mis-oriented and hold the trigger signal
while the guns/missile switch is being positioned.

This would result in the accidental expenditure of
needed munitions, and possible munition collisions
in front of the aircraft.

WEAPONS RELEASE COMPUTER SET

The weapons release computer set (WRCS) is an ana¬
log computing weapon delivery system that provides

range calculations and weapon release signals for
laydown, dive laydown, dive toss, and offset bomb
modes of weapons delivery. The system provides
steering signals and range-to-target information for
use in the target find and offset bomb modes of oper¬
ation. In addition, the WRCS provides maneuver
commands, distance to target, and a release signal
for the AGM-45 delivery mode (figure 1-45). Finally,
the system may be operated simultaneously with any
LABS bombing mode, which then becomes the LABS/
WRCS integrated mode. The target find mode is only
a navigational mode in which the system cannot de¬
liver a release signal. Hence, the net function of
this system is to direct the aircraft to a specific
ground objective (or target) along a ground track
which is projected directly through the target. Each
WRCS operating mode is thoroughly discussed in
later paragraphs. The AGM-45 function is presented
in T.O. 1F-4C-34-1-1A.

The WRCS consists of three units: the ballistics
computer; the weapons release computer control
panel (WRCS panel); and the cursor control panel
located in the rear cockpit on the right console (fig¬
ure 1-46). WRCS operating power is received from
the inertial navigation set (INS) and aircraft power
sources.

Change 8

1 -114J/(1 -114K blank)

BALLISTIC COMPUTER ADJUSTMENTS

REFER TO SECTION VI WRCS
DRAG COEFFICIENTS FOR
COMPUTER SETTING.

T.O. 1F-4C-34-1-1

The accuracy of the weapons release computer is
directly related to the input parameters received
from the inertial navigation set (INS) and other as¬
sociated systems when employed. The INS accuracy
should be at least maintained at 5.0 nautical miles of
error per hour (CEP). The ground speed indicator
error (while the aircraft is not moving) should not
be greater than 18 knots in 2 hours of navigation
time. However, a higher degree of accuracy can be
obtained which will produce greater bombing accu¬
racy. The following suggestions are offered.

Even 2 NM/hour of CEP is obtainable.

b. After each flight, the aircrew should note the
ground speed indicator error while the aircraft is not
moving; the indication should not be greater than 8
knots per hour of navigation time.

Note

Looseness in the ground speed/ground track
resolver can cause an erroneous readout;
however, the readout will be lower than
actual and should not present a problem.

c. The INS double alignment procedure outlined in
flight manual T.O. 1F-4C-1 produces greater WRCS
accuracy.

d. The boresight procedures used by the ground
crew should ensure that the radar boresight line and
the pipper line-of-sight are parallel during the air-
to-ground ranging mode.

e. The hand-set parameters on the WRCS cockpit
panels and the screwdriver adjustments made to the
computer must be accurate.

BALLISTIC COMPUTER, CP-805/ASO-91

The ballistic computer (WRCS computer) is behind
the rear cockpit. The computer contains all of the ana¬
log circuitry required to solve the bombing problem
for each WRCS delivery mode. Built-in-test (BIT)
features are incorporated to facilitate a go/no-go
check of the WRCS.

The computer has several screwdriver adjustments
(figure 1-46) under the dust cover plate that are made
by the ground crew. These adjustments are bias fac¬
tors and should not be confused with the actual
parameter. For example: Ve IS NOT the ejection
velocity of the bomb in feet per second; V e is the
ejection velocity bias factor that is selected and
applied to the computer. The drag coefficient value
(Cg which is dialed into the computer by the pilot) is
also a bias factor that varies with the type of bomb
and is related to specific V e bias setting. When Ve
is changed, the drag coefficient must be changed.

WEAPONS RELEASE COMPUTER CONTROL PANEL

The computer control panel (WRCS panel) has three
TARGET input controls, two RELEASE input con¬
trols, and a bomb DRAG COEFFICIENT input control
(figure 1-46). The panel also has a BIT control knob
that is used to select and test the go/no-go status of
the WRCS. Refer to figure 1-47, WRCS manual
inputs.

WRCS MANUAL INPUTS k .gg

DELIVERY

MODE

TARGET-FT X100

DRAG

COEF¬

FICIENT

RELEASE

N/S

DIST

E/W

DIST

ALT

RANGE

ADVANCE

MILLI¬

SECOND

RANGE
FT x 10
FT x 100

MAX SET

999

100

249

9.99

999

DIVE TOSS

DIVE LAY

LAYDOWN

. ....

OFFSET

BOMB

■ ■ ■■ .<

TGT FIND

■

AGM-45

TGT FIND/
LABS

4C-34-1 —1 -(49}

Figure 1-47

Target Range Controls

The three target inputs are used for the target finding
mode and the offset bombing mode. The distance be¬
tween the IP (identification point) and the target, with
respect to the target map coordinates, is placed on
the two distance readout displays by rotating the
adjacent control knobs. The distance is manually
placed on the readout control and is in hundreds-of-
feet. The top target distance readout control re¬
ceives the north or south distance, the lower target
distance control receives the east or west target dis¬
tance. For the offset bomb and target find mode, the
altitude value placed in the ALT RANGE control
should be either (l)the target or RIP elevation MSL ±
the D value for the planned run in altitude or (2) the
target or RIP pressure altitude. For the laydown
bombing mode, the ALT RANGE readout control re¬
ceives the range from the IP to target in hundreds-
of-feet. Either the ALT or RANGE placard is
illuminated under the panel, depending on the delivery
mode selected. The maximum setting on the target
controls is 999 X 100 feet (99, 900 feet). Tick marks
are provided on the 100-foot dial to permit inter¬
mediate settings. The dual purpose ALT RANGE
control has the following maximum settings: the
maximum ALT settings is 100 X 100 feet (10,000
feet); the maximum RANGE setting is 249 X 100 feet
(24,900 feet). The maximum setting on the N-S and
E-W DISTANCE controls is 999 X 100 feet (99, 900
feet).

When a value is inserted on the target ALT
RANGE counter other than 000, do not select
the target finding or offset bombing mode
unless; the aircraft altitude MSL is greater
than the value (times 100) or, performing
the target find/offset bomb WRCS BIT check
as presented in section n. This is necessary
to prevent possible damage to the pitch servo
in the WRCS computer.

1-116

Change 5

T.O. 1F-4C-34-1-1

ReUase Rang* Control

The release range (Rr) control knob is used to man¬
ually set the bomb range in tens-of-feet on the digital
readout. This control is used for the laydown, dive
laydown, and offset bombing modes. The maximum
setting is 999 X 10 feet (9,990 feet).

Not*

I * As described later, the (Rr) setting may be
as great as 99, 900 feet for WRCS/AJB-7 in¬
tegrated deliveries.

•Do not set the target range control and re¬
lease range control on equal values, allow at
least 0.25 second time/distance between set¬
tings to allow for the maximum possible
bomb rack time delay. If the values are
equal, the bomb may not release or the bomb
releases late.

Release Advance Control

The release advance control is operative in allWRCS
bomb release modes and in the WRCS/LABS integrate
mode. The release advance control can be used in
conjunction with the intervalometer on the station and
weapon selection panel to advance the release signal
in milliseconds. For example; if the BOMBS/

TRIPLE mode is selected, with a release interval of
100 milliseconds (100 MS), the WRCS normally com¬
putes the release of the first bomb-on-target. The
release advance control can be used to place the
second bomb on-target by setting 100 milliseconds
on the digital readout; the first bomb will then hit
short of the target, the third bomb will hit long of
the target. The counter has a maximum setting of
999 milliseconds. The release advance setting that
will place the middle bomb on target can be deter¬
mined by the following equation:

For an ODD number of bombs, to place the middle
bomb on target:

RA = Ir (N-l)

For an EVEN number of bombs, to place the FIRST
middle bomb on target:

RA = Ir (N-2)

For an EVEN number of bombs, to place the SECOND
middle bomb on target:

RA = Ir (N)

where:

RA = Release Advance Setting in milliseconds.

I R = Release Intervalometer setting in
milliseconds.

N-l = The number of bombs released minus
one bomb.

Drag Coefficient Control

The drag coefficient control is used only during the
dive toss mode. The maximum setting 9.99. Refer
to WRCS Drag Coefficients section VI. The drag
coefficient (Cr) is a bias factor that is analytically
established to equate the computer bomb trajectory
to the actual bomb trajectory. This drag coefficient
value is not the mathematical drag coefficient of the
bomb. The ground crew must set the Ballistic Com¬
puter (CP805/ASQ-91) in door 19. When V e is
changed, the drag coefficient will change.

Built-in-Test (BIT)

The built-in-test (BIT) control is used to establish
the go/no-go status of the WRCS. The BIT selector
knob is not a mode selector, switch for computer
operation. The BIT is initiated by rotating the knob
to the bombing mode to be tested and depressing the
button in the center of the selector knob, placarded
PUSH FOR BIT, wait 5 seconds and then depress the
FREEZE button while holding the BIT button de¬
pressed. Upon receiving either a Go or No-Go plac¬
ard illumination, the BIT is discontinued by releas¬
ing the button. The NO-GO and GO lights are located
under the panel to illuminate the applicable placard.
Illumination of the NO-GO indicator at times other
than the BIT checks indicates an inertial navigation
system malfunction. A NO GO indication will result
if the BIT parameter (listed in the checklist) are not
used. If a NO GO indication is received as the BIT
button is released, the indication can be disregarded
if a GO indication was previously obtained. Refer to
section H, WRCS BIT check procedures.

CURSOR CONTROL PANEL

The cursor control panel (figure 1-46) contains the
additional control required to perform the target¬
finding mode and the offset bombing mode.

Cursor Controls

The cursor control panel has two thumbwheel type
cursor controls (or slew controls) placarded ALONG
TRACK and CROSS TRACK. These controls are used
to position the cursors that appear on the radar
scopes when operated in the MAP-PPI mode. The
controls are spring-loaded to return to the center
position after each operation of the control; this re¬
turn motion of the control does not affect the posi¬
tion of the radar cursors. The along track control
contains a microswitch that activates a relay to en¬
able the cursor control commands to be received by
the WRCS computer. Therefore, the along track
control must be moved first, and then the cross track
control. Until the along track control is moved, or
the freeze button is depressed, the velocity inte¬
grators in the WRCS computer are maintained at
zero distance traveled. The along track control po¬
sitions the range cursor over or below the RIP radar
return. The cross track control positions the verti¬
cal offset cursor over the REP radar return. The

Change 4

1-117

T.O. 1F-4C-34-1-1

intensity of the cursors on the scopes can be con¬
trolled by the controls located on scope panel in the
rear cockpit. If the cursors appear to be erratic in
track or control, push the reset button and resume
operation.

Note

Do not position the range cursor below zero
range. If the range cursor is moved below
zero range and positioned over the IP, the
steering information will be in error by 180
degrees and the cursor will respond opposite
to along track cursor control movements.

Freeze Button

When the freeze button is energized, the velocity
integrators in the WRCS computer begin to calculate
the distance traveled from zero, and the cursors
begin tracking the ground position indicated on the
radar scopes by the intersection of the two cursors.
The freeze button remains illuminated until the re¬
set button is depressed, or until a different delivery
mode is selected. The freeze button is used also during
the BIT check to initiate the test problem for all
bombing modes.

Target Insert Button

When the TARGET INSERT button is energized, the
north-south and east-west distances (entered in the
WRCS panel controls) are inserted into the WRCS
computer. This action causes the cursors to move
from the RIP to the target and begin tracking the
target location on the radar scope. Only at this point
is target steering information supplied to the various
display instruments. The target insert button re¬
mains illuminated until the reset button is depressed,
or until a different delivery mode is selected.

Reset Button

The reset button is a momentary pushbutton switch
spring-loaded to ON. Depressing the reset button
deenergizes the tracking relays and causes the veloc¬
ity integrators to return to zero distance traveled; the
freeze button light and the target insert button light
go out; the offset cursor on the radar scope moves to
the center of the scope; the range cursor disappears.
The purpose of the reset button is to permit the air¬
crew to cancel all previous inputs and start over.

This might be desirable when the RIP can be visually
located and a fly-over fix on the RIP accomplished.
When the aircraft is directly over the RIP, the
pilot pushes the freeze button to energize the veloc¬
ity integrators. If immediate steering information
is required, the pilot should depress the target in¬
sert button as soon as possible after depressing the
freeze button.

LEAD COMPUTING OPTICAL SIGHT

The lead computing optical sight system (LCOSS)
provides a sight aiming reference for air-to-air and
air-to-ground methods of weapon deployment. The
sight system also provides steering indications for

certain WRCS modes of operation and performs as
an indicator for certain LABS delivery modes. The
specific operating mode of the sight system is gov¬
erned by the position of the delivery mode selector
on the main instrument panel. The sight unit is
mounted on the front cockpit radar scope. A red
reticle image is projected on a combining glass to
serve as the visual sight reference. The sight can be
depressed vertically from zero mils to 245 mils be¬
low the fuselage reference line. The sight is de¬
pressed by rotating the reticle depression knob until
the digital readout (in one-mil increments) corre¬
sponds to the desired sight setting. The sight cannot
be manually positioned in azimuth.

The optical sight has two modes of operation: A/G
(air-to-ground) and A/A (air-to-air). Variations of
the two basic modes are controlled by the position of
the delivery mode selector. Figure 1-48 is a table of
optical sight functions vs the selection of the various
delivery modes before the modification of T.O. 1F-
4E-556. Figure 1-49A is a table of optical sight
functions after T.O. 1F-4E-556.

The reticle image is composed of a fixed reticle, roll
reference tabs, and a range bar (figure 1-49). The
fixed reticle consists of a two-mil diameter pipper
located in the center of a 25-mil diameter segmented
circle, and a 50-mil diameter complete circle. The
50-mil circle has three index tabs located on the
outer edge at the top, and left and right of the pipper.
The roll reference tabs rotate about the 50-mil circle
and basically have two separate functions. During the
offset bombing mode and the target finding mode, the
roll tabs provide steering information supplied by the
WRCS. The position of the roll tabs, with respect to
the fixed index tabs, indicates the angle between the
ground track and course to the target. During all
other modes of operation, the roll tabs indicate the
aircraft roll attitude which is supplied by the INS.

1-118

Change 5

99 999 99

T.O. 1F-4C-34-1-1

OPTICAL SIGHT FUNCTIONS

OPTICAL SIGHT RETICLE

RBL = Radar Boresighl Line FRL = Fuselage Reference Line. NA = Not Applicable.

The lead computing function of the optical sight reticle is not altered by the delivery mode selector panel selection, nor by the selec¬
tion of GUNS & STORES. The master arm switch must be in ARM (see T.O. IF—4E—534). When the ARR button Is held depressed,
the lead angle computer receives a fixed 1500 foot range signal; the range bar continues to indicate the actual slant range, or the
maximum dlsplayable range of 6700 feet.

The roll tabs display roll attitude until Target Insert, then the roll tabs display steering commands to the target.

The sight reticle is pitch stabilized; manual depression is from the level plane (the local horizontal). If INS fails during LABS
mode, the AN/AJ8-7 reference system must be used; switch the attitude reference system selector knob to STBY for reliable sight
depression.

Only DIRECT position can be used to fire rockets.

The function of the optical sight depends upon the delivery mode selector panel selection (except for GUNS).

The OFF position should be selected; however AIM missiles can be launched with any position selected except LABS. The function
of the optical sight is not affected when air-to-air mode is selected.

If weapon selector knob is in GUNS, the sight functions as a combination of the delivery mode selected and GUNS A/G.

If GUNS or GUNS & STORES is selected, the master arm switch must be in SAFE to launch air-to-air missiles.

4C-34-1-M50)

Figure 1-48

Change 4

1-119

OPTICAL SIGHT RETICLES

RANGE BAR FUNCTION

2 MIL DIAMETER

50 MIL DIAMETER

* LEFT ROLL
**(OR STEER RIGHT)

* RIGHT ROLL
**(OR STEER LEFT)

* WINGS LEVEL
* *(OR ON COURSE)

* AIRCRAFT ATTITUDE
** STEERING COMMANDS FOR TARGET
FINDING OR OFFSET BOMBING MODES.

AFTER RADAR LOCK-ON
Max range 20,000 FT
triple ranging when guns A/A is not
selected.

AFTER RADAR LOCK-ON
Max range 6,667 FT
with guns A/A selected.

BEFORE RADAR LOCK-ON

Figure 1-49

T.O. 1F-4C-34-1-1

gun weapons selected and with the range bar at the 6
o'clock position, the actual range is 1000 feet. When
the range bar tab is at the 5 o'clock position the
range is 2000 feet. The range indication is linear:
i.e., 1000 feet per each number on the face of a clock.
When the range bar reaches its maximum length,

(near the 12 o'clock position), the radar range is
6667 feet If the range is greater than 6667 feet, the
range bar will remain at the maximum position.

Note

After T.O. 1F-4E-534, the lead compute
mode of the opticle sight may be obtained
with the master arm switch in SAFE.

When any other weapon or delivery method is se¬
lected (except guns), the minimum range position
represents 3000 feet; the maximum range position
of the bar represents 20,000 feet (See figure 1-49
for a summary of all sight operating modes.) The AC
may, knowing the wingspan of a target aircraft, use
the 25 and 50 mil diameter reticle rings as a quick
range reference in the air-to-air gunnery environ¬
ment. (Wingspan vs. range is explained in part 4.)

RETICLE CAGING (BEFORE T.O. 1F-4E-556)

Air Refueling Release (ARR) Button

The ARR button is used (after radar lockon) to stabi¬
lize the optical sight in the guns air-to-air lead com¬
puting mode. In air-to-air mode, the sight reticle
moves in azimuth and elevation to display the lead
angle required. Before radar lockon a pseudo-range
of 1500 feet is supplied to the lead angle computer;
the range bar is not displayed. After radar lockon,
the actual slant range to the target is supplied to the
computer and displayed by the range bar. When lock¬
on is accomplished at long ranges, the sight reticle
is over sensitive due to range, high G forces and/or
constant maneuvering flight. The sensitivity of the
reticle can be reduced by depressing and holding the
ARR button. When the ARR button is held depressed,
the lead angle computer receives a fixed 1500-foot
range signal (figure 1-50); the range bar continues to
indicate the actual slant range, or the maximum dis-
playable range of 6700 feet. When the trigger trans¬
fer relay is energized by selecting guns, the function
of the ARR button is also transferred to provide reti¬
cle caging. The ARR button will not activate the
AIM-4D coolant supply. The missile arm switch and
missile select switch may be in any position.

Other Sight Functions

The sight reticle may be used as an indicator for the
various bombing modes. For example, the sight
generally functions along with the pullup light dur¬
ing LABS bombing modes (a release indicator). The
sight flashes (ON-OFF) indicating an INS failure,
which means that the WRCS is inoperative. The reti¬
cle light also flashes if the AC inadvertently releases
the bomb button during automatic bomb release modes
where the release button signal must be held contin¬
ually (bomb run abort indicator).

RETICLE CAGE (AFTER T.O. 1F-4E-556)

Throttle Cage Button

The sight cage function is removed from the control
stick ARR button and added to the cage button on the
inboard throttle. With the sight operating in the lead
compute (GUNS) A/A mode, the CAGE signal essen¬
tially applies the same functions as the ARR button,
except the fixed range value is changed. With range
lockon, the CAGE signal energizes the reticle stiff¬
ness circuits and the sight computes lead for a
target range of 1000 feet.

Note

The AC can inadvertently break lockon by
depressing the CAGE button (with the inten¬
tion of obtaining sight stiffening) if the WSO
is locked on in the RDR mode. Depressing
the CAGE button does not break lockon if the
WSO is locked on in the BST mode and in the
5-mile range.

If the sight is being operated in the A/G mode, then
the CAGE signal provides complete sight switching
to the A/A mode. The CAGE signal switches the
sight into that A/A mode which corresponds to the
position of the guns/missile switch. With missiles
selected, the sight reticle cages at RBL. With guns
selected and while the cage button is held in, the
reticle switches to RBL. As cage is released, the
reticle goes to lead compute; either the 1000 foot
fixed range or the radar range if lockon is present
(figure 1-49 A).

LOFT BOMBING EQUIPMENT

The loft bombing delivery mode is conducted using
the following equipment:

a. Attitude director indicator (ADI).

b. Accelerometer.

c. Pullup light.

d. Bomb release angle computer (Low Angle).

e. Bombing timer (Pullup Timer).

f. Delivery mode selector knob.

g. Pedestal panel.

h. Bomb release button (pickle button).

The following describes system components which
have not been described elsewhere.

ATTITUDE DIRECTOR INDICATOR (ADI)

The ADI aids the AC in establishing and maintaining
a constant G pullup maneuver. The pointers are pro¬
grammed to move out of center when the aircraft is
not following the programmed pullup profile of 4.0 G
obtained in 2 seconds and maintained thereafter, and
a wings-level pullup. When the loft bombing mode is
performed by using a pullup acceleration of 3.0 G
obtained in 2 seconds, the ADI should not be used;
use tlie aircraft accelerometer.

Change 7

1-121

T.O. 1F-4C-34-1-1

OPTICAL SIGHT FUNCTIONS

AFTER T.O. 1F-4E-556

DELIVERY

MUNITION

SELECTED

WPN SEL

DELIVERY

OPTICAL

OPTICAL SIGHT RETICLE

POSITION

SELECTOR

MODE

ELEVATION

AZIMUTH

ROLL TABS

RANGE BAR

GUNS

Any except
TV/ARM

Lead Compute

Max Range

6700 ft

Manual Dep.
from FRL

Roll

Heat or Radar
Missiles

Any except
TV/ARM

A A

Caged at
RBL

Caged at

0°

Rockets,

GP Bombs,
AGM-12

BOMBS,
RKTS & DISP,
AGM—12, or

DIRECT

Manual Dep.
from FRL

Target Find

TGT FIND

Caged at
RBL

Caged at

0°

Offset Bomb

BOMBS, RKTS
& DISP or A

OFFSET

Max Range

Dive Toss,
Dive Laydown,
Laydown

BOMBS, RKTS

WW AG

Caged at
RBL

Drift

8. DISP or A

i»

Timed or

AN/AJB-7

BOMBS, RKTS
& DISP or

Caged at

AGM-45

Ft ARM

AGM-45

Caged at
RBL

0°

MK 1

Mod 0

O TV

DIRECT

Manual Dep.
from FRL

With lockon, the CAGE signal (held in) applies the reticle cage / 1000 ft. fixed range, lead compute mode. Without lockon, the CAGE signal
(held in) places the reticle at RBL.

A momentary CAGE signal switches the sight to A/A lead compute mode, either 1000 ft. range or at RDR range if lockon is present (switching
occurs as the CAGE button is released).

|C^ A momentary CAGE signal switches the sight to the A/A mode: either caged at RBL with HEAT/RDR missiles selected; or lead
compute with GUNS selected.

Roll displayed until target insert, then steering to target.

The sight reticle i s pitch stabilized; manual depression is from the level plane If INS fails (reticle flashes* ), the AN/AJB—7 reference
system must be used; switch the altitude reference system selector knob to STBY for reliable sight depression.

The CAGE signal places trigger circuit into either GUNS or HEAT/RDR missile fire network; the sight functions as stated in note 3.

jft The sight reticle flashes if INS fails; at AN/AJB-7 or WRCS mission abort, or with bombbutton power loss. The CAGE signal deenergizes
the reticle flasher.

4C-34 —1-1—(216)

Figure 1-49 A

1-122

Change 6

T.O. 1F-4C-34-1-1

Note

For LOFT mode of LABS delivery, the ped¬
estal panel REJECT switch should be in DF
REJ, or else the weapon selector must not
be in the AGM-45 mode. This is necessary
to get the ADI vertical pointer into the LOFT
network.

When the bomb button is depressed, the vertical
pointer centers - presenting the roll signal and in¬
dicating flight path deviations while the pullup timer
is operating. At pullup, when the pullup timer is
complete, the resolved yaw/roll signal is presented
on the vertical pointer. If the pointer deflects to the
right during the pullup, the AC rolls to the right-cor¬
recting into the pointer. The vertical director warn¬
ing flag appears or disappears to indicate the degree
of TACAN signal strength. Therefore, the appearance
of the flag has no meaning with respect to the vertical
pointer in a bombing mode.

The horizontal pointer is always deflected out of view
unless the loft bomb run is in progress (bomb button
depressed). The pointer indicates deviations in the
1.0 G flight path during the low level approach to
the pullup point. When the pullup timer is complete,
horizontal pointer movement represents error be¬
tween the desired pullup G program and actual load
factor which is measured by the accelerometer. Note
that the system actually programs the proper G
build-up rate, which means that if the AC increases
G loading at the proper rate, the pointer will never
move from the center of the sphere. The pointer
continues showing error in the constant 4.0 G flight
path until pilot releases the bomb button after final
bomb release.

The ADI OFF flag comes into view if: (1) a system ac
or dc power failure occurs; (2) there is excessive
error in the roll and pitch signal sources of the gyro¬
scope assembly; (3) an ADI failure or an internal dc
failure within the ADI occurs. The OFF flag indicates
malfunctions of the ARBCS only, regardless of the
mode the AC has selected (PRIM or STBY) on the
compass control panel. If the gyro system fails in
some manner (as suggested by conditions 1 and 2
above), the aircrew cannot expect to obtain an ac¬
curate bomb release since release occurs through
the ARBCS pitch following system.

BOMB RELEASE ANGLE COMPUTER

The release angle computer contains the high and low
angle release switches, the drum shaft and yaw/roll
resolver, and the drogue switch. The pitch inputs
drive the drum shaft which actuates the high and low
angle release switches. The yaw and roll inputs are
resolved, as a function of pitch, and transmitted to
the flight director bombing computer for use in the
vertical director pointer network. The controls on
the front of the computer are available in the rear °
cockpit. The Low Angle control may be set from 0°
to 89.9°, and the High Angle control may be set from

70° to 179.9°. Only the Low Angle control is used
for loft bombing.

WARNING

When the LABS release angle gyro is set
greater than 169.0°, bomb release may oc¬
cur at the pullup point when the bomb button
is depressed (INST O/S) or at the comple¬
tion of the Pull Up Bombing Timer (TIMED
O/S).

FLIGHT DIRECTOR BOMBING COMPUTER

This unit develops dc voltages, which are propor¬
tional to yaw/roll and G error, for steering indica¬
tions in the loft bombing maneuver. The unit also
contains the tone generator which provides the pullup
tone in the headset. By removing a cover plate, con¬
trols are available to set tone level, roll sensitivity,
yaw sensitivity, and pitch and G error sensitivity.
The sensitivity controls govern the ADI horizontal
and vertical pointer rate of deflection with respect to
yaw/roll and G error signals. The flight director
computer contains a roll cancel relay which is ener¬
gized if roll error (yaw/heading change) exceeds 30°
during the pullup flight path. With the roll cancel
circuit energized, the release circuit cannot be en¬
ergized and the bomb run is cancelled. To ready the
system for another run, momentarily position the
delivery mode selector knob out of the selected func¬
tion then back to LOFT.

BOMBING TIMER (DUAL TIMER)

The dual timer controls include the pullup and re¬
lease setting control knobs in the rear cockpit. The
pullup timer may be set from 0 to 60 seconds and the
release timer within limits of 0 to 30 seconds, each
in 0.1 second increments. The minimum setting for
either timer is 0.1 second. The setting references
in the windows do not move during the application of
timer voltage in the bomb run. This is a solid state
timer. Voltage is applied only to the pullup timer in
the LOFT or TIMED O/S modes. Li the TIMED
LEVEL and TIMED LADD mode, both timer circuits
are energized, providing the pullup timer is not set
on zero. In the TIMED LEVEL and TIMED LADD
modes, the release timer must be set to obtain the
release signal. (The release timer may be set on
zero for the LOFT and O/S modes.) Completion of
the pullup timer energizes relays which provide the
various pullup signals and the pullup flight path pro¬
gram. The bombing timers installed in these air¬
craft do not provide a pullup warning tone; only the
steady tone is available.

Note

The AN/AJB-7 tone will transmit over the
air unless the tone cutoff switch is placed
to TONE OFF.

Change 5

1 -122A/(1 -122B blank)

WEAPON DELIVERY MODES (F-4E)

T.O. 1F-4C-34-1-1

AIR-TO-AIR GUNNERY

The following aircraft equipment comprise the F-4E
air-to-air gunnery capability.

a. M61A1 Nose Gun and/or SUU-16/A SUU-23/A
Gun Pod.

b. AN/ASG-26 Lead Computing Optical Sight Sys¬
tem (LCOSS).

The aircraft systems listed below are electrically
interfaced with the optical sight system in support of
the air-to-air lead computing mode.

a. AN/ASN-63 Inertial Navigation Set.

b. A24G-34 Air Data Computer Set.

c. AN/APQ-120 Radar Set.

In the lead computing mode, the sight system solves
for a predicted point of impact by developing a solu¬
tion to the vector diagram shown in the upper part of
figure 1-50. The solution is computed in terms of
aircraft azimuth and elevation coordinates, not earth
coordinates. The net az-el solution is a function of
trajectory shift, gravity drop, and kinematic lead
vectors. The resultant is the lead angle, which is
the angle formed between the gun bore line and the
pipper sight line with the pipper on target. The vec¬
tors are briefly defined below.

TRAJECTORY SHIFT

Trajectory shift occurs because the gun bore line and
the aircraft flight path are not the same. The line of
departure of the bullets therefore forms an interme¬
diate path which is a function of the gun muzzle ve¬
locity vector, the aircraft flight path vector, and the
included angle. Since trajectory shift lies in the
pitch plane of the aircraft, the sight gyro system is
calibrated (a fixed setting for each altitude and range)
to correct for trajectory shift in the elevation net¬
work.

GRAVITY DROP

KINEMATIC LEAD

radar boresight line (RBL). In maneuvering flight,
the magnet axis follows RBL while the gyro resists
any change in direction. Since the gyro dome ro¬
tates directly in the magnetic field, an increase or
decrease in magnet current strength has a sensitivity
(precession) effect on the position of the gyro. For
example, an increase in magnet current strength—
which occurs with a decrease in radar range—causes
the gyro spin axis to precess and align more closely
with the magnet axis. The resultant gyro motion,
which is transmitted to the optical sight reticle, be¬
comes a reduction in the indicated azimuth and ele¬
vation lead as the aircraft closes with the target. As
figure 1-50 shows, the inputs which affect magnet
current strength are radar range (or the fixed reti¬
cle cage signal) and air density from the air data
computer (ADC). After T.O. 1F-4E-560, ADC angle
of attack and TAS are added inputs to enhance lead
computer operations against maneuvering targets.

To summarize optical sight lead functions, the azi¬
muth-elevation lead computations are applied in
terms of aircraft coordinates. Correction factors
are applied to influence both the gyro azimuth and
elevation output for range and air density. The ele¬
vation (pitch) output is influenced by normal acceler¬
ation from the accelerometer circuits. The net opti-
cal.sight corrections are these plus the calibrations
for gravity drop and trajectory shift. As the flow
diagram shows, the sight system provides lead data
for the constant 1500 foot range when radar lockonis
lost or when the AC actuates electrical cage. After I
T.O. 1F-4E-556, the cage signal fixed range input is I
1000 feet. With radar lockon, range data is always
available to the reticle range bar when range is
within the limits of 900 and 6700 feet. However, the
sight computes lead for a maximum range of 4000
feet. Roll reticle signals are applied directly from
the INS gyro platform.

As the AC tracks and puHs the pipper (from a point
aft of the target) up into the target, acceleration
build-up rate should be constant. Then the act of
stabilizing the pipper on target is a matter of holding
a G that has already been obtained, and for which the
sight has already compensated.

Change 5

1-123

T.O. 1F-4C-34-1-1

OPTICAL SIGHT SIGNAL FL OW

mm m m

Jr m 4c

AIR-TO-AIR MODE

EARTH

VERTICAL

■PET

ELEVATION

LEAD

-J\ —

i c An

GUN BORE LINE

TRAJECTORY SHIFT

GRAVITY DROP

KINEMATIC LEAD

INS

GYRO

PLATFORM

I ARR BUTTON I
(STICK) !|

THROTTLE

CAGE

button

I RADAR
SET

ITead computing amplifier

'-LI I

O GYR0 MAGNET CURRENT STRENGTH IS A
FUNCTION OF SUMMED RADAR RANGE, AIR
DENSITY, AOA & TAS SIGNAL INPUTS.

O AZIMUTH LEAO OUTPUT IS A FUNCTION OF
AIRCRAFT YAW RATE. THE MAGNITUDE OF
AZIMUTH OUTPUT IS CONTROLLED BY MAGNET
CURRENT STRENGTH.

O ELEVATION LEAD OUTPUT IS A FUNCTION OF
AIRCRAFT PITCH RATE. THE MAGNITUDE OF
ELEVATION OUTPUT IS CONTROLLED BY
ACCELEROMETER OUTPUT & MAGNET CURRENT

strength.

O AFTER T.O. 1F-4E-534, MASTER ARM MAY
REMAIN SAFE.

O AFTER T.O. 1F-4E-556, FIXED RANGE IS 1000 FT.
THE CAGE BUTTON IS ADDED TO THROTTLE ASSY.

AFTER T.O. 1F-4E-560.

_MECHANICAL CONNECTION

» ELECTRICAL CONNECTION

LEAD COMPUTING OPTICAL SIGHT AN/ASG-26

OPTICAL DISPLAY UNIT

28V DC AIR-TO-AIR SELECTED

MODE SWITCH

ROLL RETICLE

RETICLE

STIFFNESS

RELAY

ENERGIZED

RADAR

LOCKON

RADAR RANGE

ROLL 1 [

RETICLE 1-1. #

DRIVE UNITS .I V •'

RANGE BAR I
DRIVE UNITS f

1 1500 FT.

RANGE Jn

lETWORld

RANGE

RETICLE

^ TO RANGE ENERGIZED

"bar drive

AZIMUTH

XMTR

AZIMUTH

DRIVE

UNITS

( AZIMUTH LEAD I

AIR DATA
COMPUTER
SET

magnetic

CURRENT

MAGNETIC

CURRENT

ELEVATION

LEAD

SERVOED

MIRROR

elevation

XMTR

GYROSCOPE

Jj-EAD COMPUTING GYROS^CO

i ELEVATION
DRIVE
UNITS

=11

4C-34-l-l-(53)

Figure 1-50

1-124

Change 5

UNCLASSIFIED

T.O. 1F-4C-34-1-1

The guns are selected for firing as stated previously.
The AC selects GUNS, selects the required sta-
tions(s), and selects master arm. The weapon fires
as the AC delivers the trigger signal.

NOSE GUN SYSTEM, M61A1

The internal gun system comprises an assembly of
units in the aircraft nose section as figure 1-51 indi¬
cates. The 20mm weapon is a complete palletized
package which may be downloaded for maintenance
purposes and replaced by another complete assembly.
The system is electrically controlled and hydrauli¬
cally powered with a capability of two rates of fire;
the AC may select firing rates of either 6000 SPM
(shots per minute) or 4000 SPM. The total ammuni¬
tion capacity of the system is 639 rounds. The fol¬
lowing list includes some of the major components of
the gun system and the associated aircraft power re¬
quirements.

a. The M61A1 gun.

b. The ammunition drum, including the mechani¬
cally driven entrance and exit units and feed chutes
which accomplish munition transfer.

c. Hydraulically operated gun scavenge system,
which removes gun gas from the gun compartment by
opening the scavenge door during and approximately
30 seconds after each gun burst.

d. The gun purge system, which applies engine
bleed air to an ejector system to remove gas directly
from the gun breech. The purge system functions
during and 30 seconds after each gun burst.

e. The gun hydraulic system, which consists of a
solenoid controlled two-level flow valve in the air¬
craft; a solenoid operated gun control valve which
also functions as a brake during gun deceleration;
and a hydraulic motor which drives the gun. The
aircraft utility hydraulic system is used to operate
the gun system.

f. The gun control unit - an electrical control net¬
work which contains the necessary circuits to dis¬
perse gun operate and fire signals. The control unit
receives aircraft voltage through energized cockpit
gun controls, gun power circuit breakers, and the
trigger switch.

SYSTEM COMPONENTS AND OPERATION

The AC operates the gun system through the nose gun
select, station select, and master arm controls on
the pedestal panel. Gun master arm voltage is avail¬
able only if the landing gear handle is UP.

Ammunition Drum and Conveyor System

The drum assembly (figure 1-51) provides the stor¬
age area for the 20mm ammunition and is directly
linked to the ammunition feed conveyor system and
the return conveyor system. Each conveyor system
is identical and contains an exit unit for removing
ammunition from the drum, and an entrance unit for
returning spent round cases into the drum. The in¬
ner drum assembly, which is mechanically driven,
rotates and drives ammunition along drum partitions
and into the exit unit. The exit unit removes the
rounds from the drum partitions and passes them on

to the conveyor which supplies them to the gun feed
assembly. After firing, the conveyor system directs
spent cases (and cleared rounds) to the drum en¬
trance unit. The entrance unit returns the rounds
into the drum partitions. Hence, the complete am¬
munition cycle forms a closed loop.

The drum exit unit contains a last round sensing
switch. When empty rounds appear in the path of the
exit unit, the switch opens and automatically deener¬
gizes the trigger fire circuit to stop gun operation.
This also deenergizes the nose gun station select
amber light.

Hydraulic Drive Assemblies

The utility hydraulic system supplies the power to
operate the gun system at firing rates of 4000 or
6000 SPM. The rate of fire is controlled by a two-
speed hydraulic flow control valve in the aircraft,
which in turn is controlled by the Rate switch on the
pedestal panel. The application of the trigger signal
opens the gun control valve which allows power to
drive the gun system through the hydraulic motor and
gearbox.

Scavenge System

The gun compartment scavenge system includes a
scavenge door on the upper surface of the aircraft
nose section and the associated valve and linkages
that apply utility hydraulic system pressure to the
door operating valve. The door is held closed by hy¬
draulic pressure. The trigger signal drops electri¬
cal power from the valve which removes the hydrau¬
lic lock and the door opens by spring force. The door
remains open during gun firing and for approxi¬
mately 30 seconds after trigger release. If the AC
deenergizes the gun select/arm controls during the
30 second period, the door will close. With the door
open, the atmosphere within the nose section com¬
pletely changes at a rate of 1.0 to 2.0 times per sec¬
ond depending on present airspeed.

Gun Purge System

The gun purge system operation is coincident with
the scavenge system operation above. The electri¬
cally operated shutoff valve in this system, however,
controls the application of engine bleed (rain re¬
moval) air to a jet pump in the gun gas discharge
line. If electrical power is lost at the valve, the
valve fails in the open (safe) position so that the
purge system continues to function. If the AC must
dump cockpit pressure for any reason, then purge
system air is lost. In such a situation, the scavenge
system continues to function and there is no danger
of explosion or fire due to gases collecting in the
nose gun area.

GUN ELECTRICAL CONTROL

The electrical requirements for gun operation are
supplied by the aircraft main bus system and dis¬
persed by the gun control unit. The trigger signal
applies voltage to the hydraulic motor solenoid that
initiates the hydraulic gun drive force. The trigger

1-125

NOSE GUN INSTALLATION

SA F|N6 SWITCH

1 _

T.O. 1F-4C-34-1-1

also closes relays in the gun control unit that apply
240 volt dc (rectified 115 volt ac) into the round fir¬
ing circuit. Other control unit circuits include those
that control speed sensing, rounds limiter, and auto¬
matic gun clearing.

The gun always operates in an auto-clear mode.

(The auto-clear switch on the pedestal has no func¬
tion in nose gun operations.) During gun firing, the
clearing device receives a signal from the speed
sensing circuits at a frequency which is directly pro¬
portional to the rate of weapon fire. When the AC
releases the trigger, the clearing signal device pre¬
vents the gun from going into the clearing mode until
the firing rate has decelerated below 4000 SPM.

Round firing voltage is held on the gun during the
clearing cycle so that any rounds chambered before
the bolts retract are fired. The delay between trig¬
ger release and the point at which all the bolts are
cleared is such that approximately 5 to 11 rounds
will fire after the trigger is released. (This depends
on the initial firing rate.) Further, the time period
between the last round fired and complete gun stop
results in live rounds (4 to 9) clearing the gun and
returning to the drum. The total time period be¬
tween trigger release and gun full stop is slightly
less than one second. During this period, the trigger
is disabled and the AC must delay at least this long
between bursts.

Rounds Counter

The clearing signal device, which supplies signals
proportional to rate of fire, is also used to operate
the remote rounds counter on the pedestal panel. The
counter system is triggered once for every tenth
round cycled through the ammunition feed system.

Rounds Limiter

The rounds limiter device (figure 1-51) on the gun
system may be adjusted by armament crew personnel
when it is necessary to limit the quantity of rounds
to be fired during one flight. The device has a counter
unit which is set to actuate a rounds limit switch and stop
gun operation after the determined number of rounds
have been fired. After T.O. 1F-4E-528 (blocks 31
thru 40), and in block 41 and subsequent aircraft,
actuation of the rounds limit switch will deenergize
the amber light in the nose station select button.

I On modified F-4E aircraft (T.O. 1F-4E-556), actua¬
tion of the guns limit switch deenergizes the heads-
up GUN light and the nose gun station amber light.

NOSE GUN CONTROLS

Gun Select Controls
(Before T.O. 1F-4E-556)

On the pedestal panel, the AC may select the gun
weapon system either through the GUNS position on
the weapon selector knob, or by selecting GUNS and
STORES on the gun toggle switch. In the former
case, only gun armament can be fired (nose gun in¬
cluding any gun pods aboard). By using the toggle
switch, both the gun firing and conventional bomb

release circuits may be activated provided the
weapon selector is positioned for other armament.
When the weapon selector is used for guns, a reticle
alignment signal is directed to the optical sight so
that sight A/A operation is not influenced by other
weapon controls. With the sight in the A/G mode,
however, sight operation is dependent upon the po¬
sition of the delivery mode selector knob on the main
instrument panel.

Guns Missile Switch
(After T.O. 1F-4E-556)

The guns select functions are provided by the guns/
missiles switch on the left throttle. The rear-most
position of the switch selects the nose gun and il¬
luminates the heads-up GUN light. Further gun arm
functions are provided by the controls below.

Nose GunStation Select

Depressing the nose gun station select button elimi¬
nates one interlock in the nose gun select circuits
and illuminates the green light in the button housing.
The amber light in the button, which is a fire ready
indicator, will not illuminate until all gun arm inter¬
locks are removed.

Master Arm Switch

Selecting the arm position on the master arm switch
energizes all gun select circuits and arms the trigger
switch (provided the controls above are energized).
Gun firing voltage may now be applied by depressing
the trigger. The amber light illuminates to show the
ready condition. The amber light is electrically lo¬
cated so that the last rounds switch must be closed
for the light to illuminate, and rounds must not be
limited. Therefore, the light goes off when all ex¬
pendable rounds have been fired.

After T.O. 1F-4E-556, the fire-ready indication is
provided by the station ARM light and the heads-up
ARM and GUN lights. In these aircraft, the GUN
and station ARM light also deenergize to indicate
the rounds limit or last round circuit activation.

Note

After T.O. 1F-4E-534, the sight lead com¬
pute mode may be operated with the master
arm switch in SAFE.

Rate Switch

Once the master arm switch is on, power is available
for the rate switch. The rate switch LOW position in
turn controls power to the two-speed hydraulic flow
valve. In HIGH (which is the OFF position), the valve
circuit is open and the gun fires at 6000 SPM. The
LOW position (ON) energizes the low flow rate and
the gun fires at 4000 SPM.

Trigger Switch

Only the forward trigger switch controls gun firing.
The trigger signal energizes a relay in the gun con-

Change6

1-127

T.O. 1F-4C-34-1-1

trol unit which completes the round firing circuit.

The trigger signal also operates the speed sensing,
automatic gun clearing system, and the hydraulic
drive solenoids. The gun accelerates to the selected
rate of fire in approximately 0.5 second.

With the addition of the optical sight camera (T.O.
1F-4E-558), the trigger becomes a double detent
switch referenced here as trigger 1 and trigger 2.

The trigger 1 position operates the camera without
munition expenditure; trigger 2 fires the gun and
operates the camera. Refer to Opticle Sight Camera,
this part.

OPTICAL SIGHT/GUN FIRING

The nose gun is harmonized with the optical sight for
an optimum firing range of 750 yards (2250 feet).
During harmonization, the sight is depressed 2.0°
from fuselage reference line. Hence, during strafing
missions, the AC must place at least 35 mils into
the sight depression control, plus any additional
correction for factors such as ballistic drop. Refer
to the gun firing tables in T.O. 1F-4C-34-1-2. In an

air-to-air situation, the sight is operated in the A/A
mode to obtain the lead computing optical sight func¬
tions. A description of all optical sight operating
modes is provided in this section.

GUNS/MISSILE SWITCHING (BEFORE T.O. 1F-4E-556)

To further demonstrate the above controls, suppose
the aircrew is initiating an attack using air-to-air
missiles. The optical sight is caged at RBL in the
A/A missile operating mode. On the pedestal panel,
the AC may pre-select master arm and depress the
nose gun station select button. In this case, the guns
switch must be left off as long as the aircrew intends
to fire missiles. (With guns selected and master arm
energized, the trigger/missile fire circuits are
locked out.) If for any reason, the missile attack is
unsuccessful, the AC may immediately place the
guns switch on. The trigger circuits transfer from
missiles to gun firing and the optical sight automati¬
cally enters the lead compute operating mode. The
aircrew maintains the original radar lockon and
closes with the target.

1-128

Change 6

T.O. 1F-4C-34-1-1

Once the range has decreased to approximately 2
radar miles or less (12, 500 feet), the aircrew has
the prerogative of selecting R1 and switching into
radar BST mode. This provides the auto-acquisition
capability for the AC. Auto-acquisition functions and
associated limitations are more adequately described
in T.O. 1F-4C-34-1-1 A. Actual lead computing func¬
tions of the sight are available at a maximum range
of 4000 feet. Hence, the AC may hold the cage func¬
tion (ARR button depressed) to stabilize the reticle
until range becomes 4000 feet or less. At 4000 feet,
the reticle range bar reaches the 3 o'clock position.

GUNS/MISSILE SWITCHING (AFTER T.O. 1F-4E-556)

With modified F-4E aircraft, the AC may switch
from HEAT or RDR missiles to GUNS by moving the
guns/missile switch to the aft position. The optical
sight also switches from A/A missiles (RBL) to A/A
lead compute. Applying the CAGE signal switches the
radar to BST mode, range R1 and with auto-acquisi-
tion available. With the CAGE signal held, the sight
computes for the 1000 ft. fixed range.

| WINGSPAN VS. RANGE

In any air-to-air gunnery situation where radar lock-
on is not obtainable (range bar not available), the 50
and 25 mil reticle rings may be used as reference in
estimating target range. The estimated range is a
function of the known wingspan of the target and dia¬
metric dimension of the reticle rings. In part 4, a
graph of wingspan vs sight dimension (mils diameter)
is provided for target ranges of 1000 through 4000
feet, including the gun harmonization range of 2250
feet. The AC will recall that in situations where
lockon is not possible, the sight system functions as
if range is a continual 1500 feet - regardless of ac¬
tual range (figure 1-50).

Note

A description of gun harmonization methods
is provided in section IV, Supplementary
Data.

DIRECT DELIVERY MODE

When the DIRECT position on the delivery mode se¬
lector panel is selected, the bomb button is in direct
control of the bomb release relay. The DIRECT po¬
sition must be used to fire rocket launchers. De¬
pressing the bomb button releases the bombs, fires
rockets or launch the air-to-ground missiles from
the selected stations. The direct delivery mode re¬
quires that the preplanned release parameters for the
mission be established and controlled by the aircrew:
the WRCS is not used. The air-to-ground mode of
the optical sight is used to establish the bomb release
point for a given release altitude, release airspeed,
and dive angle.

DIVE TOSS BOMBING MODE

The WRCS dive toss bombing mode is a visual de¬
livery mode used to deliver the low drag bombs.

Since preplanned release parameters are not re¬
quired, the target may be approached from any di¬
rection, airspeed, and dive angle. The bomb will be
automatically released when the bomb trajectory
intercepts the target. Figure 1-52 illustrates the
various delivery maneuvers that can be used with
the dive toss mode: dive-level, dive-glide, or dive-
toss. This manual presently contains the data re¬
quired (drag coefficients) to deliver bombs using the
dive-toss bombing mode.

The AN/APQ-120 radar set is operated in the AIR-
GRD mode and in the R1 range to provide a drift
stabilized, boresighted antenna. The radar supplies
slant range information to the WRCS computer and
the optical sight. The lead computing optical sight
is used to visually establish a radar fix on the target.
The sight is operated in the air-to-ground mode to
provide roll reticle display and provide a sight reti¬
cle which is electrically caged in elevation to the
radar boresight line (depressed 35 mils from the
fuselage reference line) and drift stabilized in azi¬
muth. The dive toss bombing mode is selected by
placing the delivery mode selector knob to DIVE TOSS
and positioning the weapon selector knob to BOMBS/
RIPPLE, TRIPLE, or SINGLE. The only controls
used on the WRCS panel are the drag coefficient con¬
trol and, if required, the release advance control.

Use of the R2 and R3 range is not recommended since
the position of the ground return line sometimes
causes inadvertent side lobe lockon.

Note

With the weapon selector knob in any position
other than BOMBS, the sight depresses ac¬
cording to any MIL setting causing a gross
error unless the MIL setting is zero.

After the target area has been visually identified, the
AC begins to dive toward the target. The slant range
(roll-in altitude) is normally 20 percent higher than
it would be for direct dive delivery mode to allow
time for the accomplishment of air-to-ground lockon
by the pilot. Target tracking is not required prior to
radar lockon, i.e., the objective is to maneuver the
aircraft to obtain a strong ground return on the radar
scope which the pilot will use to obtain a lockon. The
radar range may be greater than the maximum range
display capability of the range bar; thus, the maxi¬
mum length of the range bar will be displayed. Refer
to optical sight display.

Observe the range bar for a false tracking indication.
If a rapid decrease in range is displayed, the pilot
may have locked on a radar side lobe rather than the
main radar beam. Immediately request the pilot to
break-lock for another attempt if time permits.

Not*

Lockon can be broken after the bomb button
is depressed without affecting bombing ac¬
curacy.

Change 5

1-128A/(1-128B blank)

T.O. 1F-4C-34-1-1

The AC should strive for a straightline ground track
which is projected through the target. The roll tabs
on the sight reticle will assist the AC in maintaining
a wings-level dive. The bomb button must be de¬
pressed (and held depressed until bomb releasejwhen
the pipper is on or slowly passing through the target.

Note

•if it is apparent that the drift stabilization
portion of the sight is malfunctioning, a
delivery can be accomplished with the sight
caged and an estimated wind correction offset
aimpoint used.

•The bomb button signal may be delivered at
maximum slant ranges of 25, 000 feet, and at
a maximum altitude of approximately 18, 000
feet AGL. The profile in figure 4-6 shows
expected computer accuracy under these
parameters. The profile considers only com¬
puter accuracy, and that computer inputs from
all other systems are within specified limits.

After the bomb button is depressed, the AC begins
the desired delivery maneuver: dive-level, dive-
glide, or dive-toss. The vertical needle on the ADI
displays deviations from the magnetic heading estab¬
lished at pickle. The dive-toss maneuver consists of
a pullup maneuver (at the desired acceleration rate)
that is initiated after depressing the bomb button.

The climb angle must not be greater than 10° prior to
release to ensure the accuracy of the bomb release
point. The dive-glide maneuver consists of a shallow
dive toward the target until bomb release occurs.

For example: If the initial dive angle was 40° when
the bomb button was depressed, the dive must be de¬
creased by a minimum of 5° (40° -5° = 35°) for low
drag bombs. If the initial dive was 30°, then the
dive-glide maneuver must be a 20° dive or (30° -10° =
20 ). The dive-level maneuver consists of a level
flight approach toward the target until the bomb re¬
lease occurs. The dive-toss, dive-glide, and the
dive-level maneuvers are illustrated in figure 1-52.
The WRCS function and requirements are the same
as for the dive toss maneuver. The requirements of
the dive-glide and dive-level maneuvers are:

a. The bomb button is normally depressed when the
aircraft is at a greater slant range from the target
than is required for the dive-toss maneuver.

b. The aircraft will maintain wings level flight
(after depressing the bomb button) for a longer period
than is required for the dive-toss maneuver.

When the AC depresses the bomb button, the position
and attitude of the aircraft, with respect to the tar¬
get, is set into the weapons release computer. The
slant range to the target, obtained by the AN/APQ-
120 radar, is resolved with inputs from the INS to
establish the ground range and altitude above the
target. The weapons release computer begins to in¬
tegrate ground speed and subtract the results from
the initial ground range. Vertical velocity is also
integrated and the results are subtracted from the
initial altitude above target. The weapon release
computer continuously monitors the aircraft altitude

and ground speed and automatically supplies a release
signal when the computed trajectory of the bomb in¬
tersects the target.

AIR-TO-GROUND LOCK-ON

The ALR-GRD radar mode is used only for the dive
toss and dive laydown bombing modes. The radar
AIR-GRD mode establishes the slant range to the
target and route this range data to the WRCS. The
WRCS then computes the position of the aircraft with
respect to the target and automatically releases the
bomb when the target is within bombing range.

Prior to the bombing run, the AC selects one of the
dive delivery modes on the delivery mode selector
panel, selects the A/G optical sight mode, and pre¬
pares the pedestal panel for a weapon release. The
pilot places the radar power switch to OPR, the radar
range switch to Rl, and the radar mode switch to
AIR-GRD. The radar antenna and the optical sight
are now drift stabilized; the optical sight line is par¬
allel with the radar boresight line (the centerline of
the radar beam). The B-sweep (and range strobe)
is offset from the center of the scope equal to the
drift angle.

After the target area has been visually identified, the
AC begins to dive toward the target. When the dive
angle is established and the range rate is relatively
constant, the pilot may begin the air-to-ground lockon
procedure. The receiver gain is reduced to eliminate
the radar side lobe return, thereby eliminating the
altitude line displayed on the B-sweep. The gain
should be reduced until the length of the ground re¬
turn in the B-sweep is as short as possible before the
return begins to break up and fade. The fine adjust¬
ment knob on the receiver gain control will aid the
pilot in this task. The actual length of the return is
a function of the antenna graze angle (aircraft dive
angle) and the amount of receiver gain. For a 25°
dive angle, the main beam clutter band can be re¬
duced to approximately 1/2-mile long. The clutter
band is longer for the lower dive angles.

The center of the main beam clutter band displayed
on the scope is the point on the ground receiving the
highest concentration of energy — the center of the
radar beam. This is also the point on the ground
seen by the AC through the optical sight pipper posi¬
tion.

Adjust the receiver gain until the smallest amount of
clutter is present. The acquisition symbol should be
positioned at approximately 4 miles and lockon should
not be attempted until the clutter is in this area.

Then depress the action switch to Half-Action. The
range strobe will then appear between the acquisition
symbol if there is no aircraft drift (or next to the
acquisition symbol if there is drift). Slant range is
supplied to the computer when the range strobe is
on the scope. Move the hand control to position the
range strobe directly in the center of the main beam
clutter band; then depress the action switch to Full-
Action to obtain radar lockon. However, prior to
lockon the receiver gam must be reduced to elimi¬
nate the radar side lobe return or false tracking

1-129

T.O. 1F-4C-34-1-1

OPTICAL SIGHT:

1. Drift Stabilized

2. Reticle caged to the
radar boresight line.

VISUALLY TRACK
TARGET MOMENTARILY

GROUND TRACK THRU TARGET

WRCS Manual Inputs:

1 . Drag coefficient (not set less than 1 .00)
2. Release Advance.

AUTOMATIC BOMB
RELEASE-1

DEPRESS AND
HOLD BOMB
RELEASE BUTTON

AN/APQ-1P0 MODE

1. A/G

2. Al Range

RELEASE BOMB
BUTTON AND
INITIATE ESCAPE

INS Supplies:

1. Groundspeed

2. Pitch Angle

3. Vertical Velocity

PIPPER SIGHT LINE
AND RADAR ANTENNA
BORESIGHT CENTERLINE

RADAR CONICAL
SCAN PATTERN

TARGET

'OOWN

-orrsr #om»

SIGNAL

AN/APQ-120
AIR-TO-GROUND
MODE

MMM

■

It B

WRCS CONTROL PANEL

BOMB RELEASE
BUTTON

SLANT RANGE

WEAPONS
CONTROLS AND
RELEASE NETWORK

INERTIAL

NAVIGATION

SET

L-130

T.O. 1F-4C-34-1-1

DEPRESS BOMB
BUTTON AND
DECREASE
DIVE ANGLE —

VISUALLY TRACK
TARGET MOMENTARILY

TRIPPLE OR RIPPLE
RELEASE

NOTE

PIPPER AND

RADAR

CENTERLINE

RELEASE BOMB
BUTTON AND
INITIATE ESCAPE

AUTOMATIC
ADVANCED BOMB
RELEASE POINT

AFTER DEPRESSING BOMB BUTTON:
45° DIVE; NOSE UP 5° MINIMUM
30° DIVE; NOSE UP 10° MINIMUM

TARGET

VISUALLY TRACK
TARGET MOMENTARILY

RELEASE BOMB BUTTON
AND INITIATE ESCAPE-

^— DEPRESS BOMB BUTTON
AND INCREASE DIVE ANGLE

MAINTAIN THE
GROUND TRACK
THROUGH THE
TARGET

RIPPLE RELEASE

LEVEL APPROACH TO THE TARGET
(GROUND TRACK THROUGH TARGET)

AUTOMATIC ADVANCED
BOMB RELEASE

PIPPER AND RADAR CENTERLINE

III /

/ .target/ /

1 / /CENTER sf

Figure 1-52 (Sheet 2 of 2)

1-131

T.O. 1F-4C-34-1-1

1/2 PATTERN*-1

RELEASE RANGE '

F4E-34-I-316

Figure 1-53

could result. False tracking occurs when the radar
has locked on the side lobe instead of the mainbeam.
When this occurs, the range bar on the optical sight
displays a rapid decrease in slant range. If time
permits, the following corrective action should be
taken immediately:

a. Depress the action switch to Half-Action and re¬
lease the action switch: lockon is broken.

b. Adjust the receiver gain.

c. Depress the action switch to Half-Action and po¬
sition the range strobe in the exact center of the
ground return.

d. Depress action switch to Full-Action and release
the action switch. Confirm the lockon after the ASE
circle and Skin Track light is obtained.

Range tracking of the ground return can be rejected
by depressing the action switch momentarily to Half-
Action. When lockon is broken, the ASE circle and
the range strobe is removed from the display, the
acquisition symbol reappears and the Skin Track
light goes out.

DIVE LAYDOWN BOMBING MODE

The dive laydown bombing mode is illustrated in fig¬
ure 1-53. The dive laydown bombing mode is essen¬

tially the same as the dive toss bombing mode (dive-
level maneuver) with the following exceptions for the
dive laydown mode:

a. The dive laydown bombing mode is used primarily
for the delivery of high drag weapons (CBU-1.

CBU-2, Snakeye I, etc.) where bomb range is rela¬
tively insensitive to deviations from the preplanned
release parameters.

b. The bomb range is manually set in the Release
Range control on the WRCS panel: the Drag Coef¬
ficient control is not used.

c. The AC must fly the preplanned released true
airspeed (or ground speed) and the preplanned release
height above target that will produce the bomb range
set in the Release Range control.

The dive laydown bombing mode is selected by plac¬
ing the delivery mode selector knob to DIVE LAY and
positioning the weapons selector knob to either RKTS
& DISP (for dispensers only) or BOMBS. The only
controls used on the WRCS panel are the release
range control, and if required, the release advance
control. The value placed on the release range con¬
trol is the horizontal bomb range for a given release
altitude above target AGL and release true airspeed
obtained from the bombing tables.

1-132

T.O. 1F-4C-34-1-1

L AY DOWN BOMBING MOVE /;

OPTICAL SIGHT:

1. Drift and Pitch Stabilized

2. Reticle depression controlled
by RETICLE DEPR knob.

INS Supplies:

1 . Groundspeed
WRCS Manual Inputs:

1 . Target Range
2. Release Range

Note

An IP may be used to establish the
target range if the optical sight is not used.

Figure 1-54

The initial portion of the delivery prior to depressing
the bomb button is identical to the dive toss-bombing
mode, refer to dive toss bombing mode, this section.
Depressing the bomb button causes the AN/APQ-120
radar to supply slant range to the WRCS computer
and causes the INS to supply ground speed and pitch
angle to the WRCS computer. These inputs are used
to compute the horizontal distance to the target. The
WRCS computer continues to monitor the horizontal
range to the target with respect to the initial range
established when the bomb button was depressed.
When the aircraft is at the release range from the
target set in the release range control, the WRCS
automatically supplies a release signal to the weap¬
ons release circuits.

LAYDOWN BOMBING MODE

The laydown bombing mode (figure 1-54) is used for
delivery of high drag weapons where the bomb range
is relatively insensitive to variations in preplanned

release conditions. The maneuver consists of a lqw
level approach and delivery at a preplanned release
altitude AGL and at a preplanned airspeed. The AN/
APQ-120 radar is not employed by the laydown bomb¬
ing mode. The lead computing optical sight can be
used, or an IP can be used, to establish a known
aircraft-to-target distance. The lead computing op¬
tical sight is operated in the A/G mode. With the
laydown bombing mode selected, the reticle image
will be pitch stabilized with reference to the hori¬
zontal plane of the inertial platform and drift stabi¬
lized along the ground track. The reticle depression
is controlled by the reticle depression knob.

During mission planning, a desirable sight depression
angle for the planned release altitude is chosen from
the sight depression chart; (do not add fuselage angle
of attack) the resulting range from the aircraft to
target is established and entered in the target range
control (placarded ALT RANGE) on the WRCS panel.
The horizontal bomb range for the selected release
altitude and airspeed is obtained from the bombing
table and entered in the release range control on the
WRCS panel. For the CBU delivery, or a ripple re¬
lease, one-half of the pattern length may be added to
the value placed in the range control, thereby, plac¬
ing the center of impact on-target.

1-133

T.O. 1F-4C-34-1-1

When the bomb button is depressed the aircraft will
be at the distance from target set in the target range
control, the INS begins to supply ground speed data
to the weapons release computer, and the ground-
speed data is integrated with time by the computer to
establish the distance traveled from the point. When
the aircraft has traveled the distance entered in the
target range control minus the value set in the re¬
lease range control, a bomb release signal is gener¬
ated and routed to the release circuit to initiate a
bomb release.

The laydown bombing mode is selected by placing the
delivery mode selector knob to LAYDOWN and posi¬
tioning the weapons selector knob on RKTS & DISP or
BOMBS. On the WRCS panel, enter the preplanned
values in the target range control (the Range light
under the ALT RANGE placard will illuminate when
LAYDOWN is selected) and the release range control.
The release advance control may also be used, if
necessary.

OFFSET BOMBING MODE

The offset bombing mode (figure 1-55) provides the
aircraft with an all weather (blind bombing), high
and low altitude, level bombing capability. The off¬
set bombing mode requires an IP to establish the po¬
sition of the aircraft with respect to the target. After
the aircraft position is supplied to the WRCS com¬
puter, steering information is presented to the air¬
crew. The navigation range from this point to bomb
release can be from 500 to 180, 000 feet. When the
aircraft is at the preset release range from the tar¬
get, the bomb is automatically released. To provide
an IFR capability, either the target or the IP must
be radar definable. A radar definable IP is referred
to as a radar IP (RIP). To provide a VFR capability,
a prominent visual IP (VIP) must be used. The RIP
can be beyond the target or offset from the approach
course to the target - RIP-flyover is not required.

The AN/APQ-120 radar set is not used when a VIP
is used; the aircraft must be flown directly over the
VIP to establish the aircraft position with respect to
the target — the approach can be made from any di¬
rection. The final portion of the bombing run prior
to bomb release is performed at the preplanned re¬
lease speed and level approach altitude above target
AGL. The release altitude is normally between 50
to 1000 feet; however, the release altitude can be as
high as 50, 000 feet if the bomb range does not exceed
the release range control setting on the WRCS panel
(X10 or X100).

muth, and to the radar boresight line in elevation.

The roll tabs on the optical sight can be used to pro¬
vide steering information that will guide the AC to the
target: the ADI is the primary steering instrument.
The radar is stabilized in drift, roll, and pitch. The
radar is used to identify the RIP and establish the
aircraft position with the aid of the cursor control
panel.

After target insert, the drift stabilized MAP-PPI
radar display can be used as the primary steering
instrument by flying to center the offset cursor on its
ZERO azimuth position. Also, after target insert,
the radar should be switched to minimum scope range
to further increase bombing accuracy. Before using
the scope display as the primary steering instrument,
the aircrew must establish the ZERO azimuth posi¬
tion of the offset cursor by performing the WRCS BIT
check.

The WRCS computer receives manual inputs from the
WRCS control panel. The IP pressure altitude (or IP
altitude MSL) is placed in the readout control plac¬
arded ALT RANGE (the ALT light illuminates when
OFFSET BOMB or TGT FIND is selected). The re¬
lease advance control is set (if required), and the
release range of the bomb is set in release range
readout control. The position of the target with re¬
spect to the IP and the map coordinates is manually
inserted in the WRCS control panel. For example,
the target is located a number of feet north or south
of the IP, and the target is located a number of feet
east or west of the IP as measured on the target map
or photos. (Refer to figure 1-56, IP selection area.)
When the target presents an identifiable radar return
and is used as the RIP, the target range readout con¬
trols must be set equal to zero, and the target pres¬
sure altitude (or target elevation MSL) must be set in
the ALT RANGE readout control.

CAUTION {

When a value is inserted on the target alt
range counter other than 000, do not select
the target find or offset bomb mode unless;
the aircraft altitude MSL is greater than the
value (times 100), or the aircrew is perform¬
ing the target find/offset bomb BIT check as
presented in section II. This is necessary to
prevent possible damage to the pitch servo
in the WRCS computer.

In situations where the known radar IP is actually
higher than the required approach altitude, the air¬
crew can avoid (through correct planning) any equip¬
ment damage mentioned in the caution above. Using
the following method, the mission planner determines
a reciprocal altitude/range counter setting with re¬
spect to the planned approach altitude.

a. Determine the approach altitude above MSL.

b. Determine the difference between approach alti¬
tude and the (higher) radar IP altitude (MSL).

1-134

Change 6

T.O. 1F-4C-34-1-1

c. Subtract the value of step (b) from the approach
altitude of step (a); place this amount on the ALT
RANGE counter. This establishes an IP altitude and
position which is as much below approach as the
actual IP altitude is above approach, and the radar
range to either point is the same.

d. During the mission, the AC must fly the planned
approach altitude during freeze and target insert op¬
erations to assure that correct range data is available
for the computer.

Change 6

1-134A/(1-134B blank)

T.O. 1F-4C-34-1-1

OFFSET BOMBING MOVE and
TARGET FINDING MODE

TARGET

INSERT

—target

♦ automatic

BOMB RELEASE
POINT

/ / * DEPRESS BOMB BUTTON
/ X AND HOLD DEPRESSED

/ mrm until release

' Wim If the bomb button is released,
it can be depressed again.

* OFFSET BOMBING MODE ONLY

V^* P '^^?^ECTI0N MAP - PPI MODE

/ DID I %

Pilot Detects RIP
Return on Radar
Scope

Pilot Places Cursors
Over the RIP and
Depresses the Freeze
Button.

Pilot Depresses Target
Insert Button. AC
Receives Range and
Steering Display and
Maneuvers to Target.

Maneuver Toward the
Indicator and Arrive on
Course to the Target.
NOTE: The Optical
Sight is not Drift Stabi¬
lized. PPI display
is Drift Stabil ized .

Optical Sight:

Cursor Control Panel:

1. Caged Zero 0 Azimuth .

5. Freeze Signal.

2. Reticle Depressed to the

6. Target Insert Signal.

Radar Boresight Line.

7. Cross Track Signal.

AN/APQ-120 Mode:

8. Along Track Signal.

1. MAP-PPI.

9. Reset Signal.

2. Al Range.

INS Supplies:

WRCS Manual Inputs:

1. Ground Speed.

WRCS Panel.

2. Altitude MSL.

1. Target N-^E-W Distance .

3. Ground Track.

2 . IP Altitude MSL.

4. True Heading.

3. Release Advance.

5. Aircraft Velocity East.

4. Release Range.

6. Aircraft Velocity North.

ADI

SIGHT

HSI

BDHI

F4E-34-I-318-1

Figure 1-55 (Sheet 1 of 4)

1-135

T.O. 1F-4C-34-1-1

WITH VISUAL

IP ft-4E

Optical Sight:

1 . Reticle caged to the
Radar Boresight Line.

AN/APQ-120 Mode:

1. Not Required

WRCS Manual Inputs:

WRCS Panel

1. Target N-S/E-W Distance

2. Release Advance.

3. Release Range.

Cursor Control Panel

4. Freeze Signal.

5. Target Insert Signal.

6. Reset Signal.

INS Supplies:

1. Ground Speed.

2. Altitude MSL.

3. Ground Track.

4. True Heading.

5. Aircraft Velocity East.

6. Aircraft Velocity North.

-wQe-

DEPRESS FREEZE
BUTTON AND THE
TARGET INSERT

TARGET

* AUTOMATIC
BOMB RELEASE

* DEPRESS
BOMB BUTTON

* OFFSET BOMBING MODE ONLY

ADI

SIGHT

HSI

BDHI

Depress the Freeze Button and
the Target Insert Button when
Aircraft is over IP. Steering
Information is Displayed.

Maneuver Toward the Indicator
and Arrive on Course to the
Target. Note: The Optical
Sight is not Drift Stabilized.

Note

When over the

target,, the roll tabs rotate

and the distance counters

begin increasing in value displayed.

F4E-34-1-318-2

Figure 1-55 (Sheet 2 of 4)

1-136

T.O. 1F-4C-34-1-1

HSI INDICATIONS F -4E

FRONT COCKPIT

BDHI INDICATIONS p_ 4F

AFT COCKPIT

D Bearing Pointer: Indicates the magnetic bearing
to the target as computed by the WRCS com¬
puter and controlled by the NS/EW target dis-
tance counter.

0 Heading Marker: Indicates the magnetic head¬
ing to the target as computed by the nav com¬
puter and controlled by NS/EW target distance
counter.

E Course Arrow: Indicates the magnetic course
ol the aircraft (ground track), computed by the
nav computer; same as Course Window.

D Range Indicator: Indicates the horizontal dis¬
tance (not slant range) to the target in nautical
miles.

El Course Window: Same as Course Arrow.

Q TGT Mode Light: Illuminates when the Target
Insert button is pushed on (if the instrument
lights are ON).

H Lubber Line: Indicates the magnetic heading of
the aircraft.

j^Note^

When the aircraft is on magnetic course
to the target, the Bearing Pointer and
the Course Arrow are aligned,and the
Heading Marker is aligned with the top of
the Lubber Line.

D No. 1 Needle: Same as the Bearing Pointer
on HSI.

0 NA

E No. 2 Needle: Same as the Course Arrow on
the HSI.

D Range Indicator: Same as the Range Indicator
on the HSI.

B NA

0 NA

Q Top Index: Same as the top Lubber Line on
the HSI.

I No,e 1

When the aircraft is on the magnetic
course to the target, the No. 1 Needle is
aligned with the No. 2 Needle.

F4E-34-I-318-3

Figure 1-55 (Sheet 3 of 4)

1-137

ON COURSE WINGS LEVEL

OFFSET BOMBING MODE
DEPRESS AND HOLD BO)
BUTTON (SEE NOTE)

The ADI will provide steering information until another
delivery mode is selected or the reset button is pushed

PROPER BANK ANGLE ESTABLISHED *
(UP TO APPROXIMATELY 30 DEGREES
OF BANK)

TARGET INSERT

PROPER BANK ANGLE MAINTAINED

Figure 1-55 (Sheet 4 of 4)

T.O. 1F-4C-34-1-1

___

IP SELECTION AREA

RIP HI:

NORTH

15,000

EAST;

85,000

RIP #2:

SOUTH;

30,000

EAST;

50,000

MAXIMUM TARGET
DISTANCE SETTING
99,900 FT

TO ESTABLISH THE TARGET COUNTER
SETTINGS: “THE TARGET IS LOCATED

-FEET N OR S, AND_FEET E

OR W OF THE RIP."

?-'N

\ ip

_\ SELECTION

\ AREA

/ RIP \

- \

/ Hi \

SOUTH

A I /

30,000 FT
- 1

/ EAST 1 J

85,000 FT.- ? S

* / 1 1 1

1 ‘ 1 "'~" EAST /

/ TARGET

kbEI

NORTH

16,000 FT

i r

99,900 FT

- 75,000 FT

- 50,000 FT

-25,000 FT
OFT E

*i Cb **o l r

180,000 —■

SELECTED

APPROACH CORRIDOR

F4E-34*I-3T9

Figure 1-56

The cursor control panel is used to supply inputs to
the WRCS computer which establishes the position of
the aircraft with respect to the IP or RIP and initiate
computer operation. The use of these controls are
discussed later. The INS supplies the following air¬
craft position inputs to the computer:

a. Aircraft ground speed.

b. The velocity vectors: north-south, east-west.

c. Aircraft altitude MSL (standard day).

d. Ground track.

e. Aircraft heading.

The computer uses these signals in conjunction with
the MAP- PPI radar and the inputs from the cursor
control panel to generate the following displays:

a. The position of the slant range cursor and the
offset cursor is displayed on both radar scopes.

b. Horizontal ground range to the target is displayed
on the HS1 and BDHI instruments if the respective
mode selector switches are in NAV COMP.

c. Steering angle of the target is displayed on the
HSI, BDHI, ADI instruments, and the optical sight.

d. The bomb release signal is generated and rquted
to the weapons release circuit to release the bomb.

OFFSET RADAR IP

When using a radar IP, the offset bombing run begins
when the RIP is identified on the scope. The pilot
positions the range cursor below the RIP return by
moving the along-track control on the cursor control
panel. The cross-track cursor control is used to
position the offset cursor over the RIP radar return.
When the RIP return is at the intersection of the cur¬
sors , the pilot may push the freeze button: the cursors

1-139

T.O. 1F-4C-34-1-1

now begin tracking the RIP. After positive tracking
of the RIP is established and the aircraft is within
180,000 feet from the target, the pilot may push the
target insert button; the cursors automatically center
over the target and begin tracking the target. The
cursor controls can be operated at any time prior to
Target Insert to update (touch-up) the position over
the RIP. If the target can be defined on the radar
scope, the cursor controls can be operated after
Target Insert to update on the target, providing the
RIP altitude is the same as the target altitude. When
there is a difference between the RIP and target alti¬
tude, the target pressure altitude (or target elevation
MSL) should be placed in the ALT RANGE readout
control prior to updating on the target.

If a visual flyover fix on the RIP is desired after the
cursors are tracking the target, the pilot must push
the reset button and then, when the aircraft is directly
over the RIP, the freeze button and the target insert
button are depressed simultaneously. Steering infor¬
mation will be presented to the AC on the ADI, the
HSI, and the optical sight. Steering information is
supplied to the pilot on the BDHI. The AC should use
the ADI as the primary instrument to maneuver the
aircraft on course to the target. Refer to figure
1-55, sheet 4.

Note

ADI steering will not be available if the

weapon selector knob is on AGM-45.

After the target insert button is depressed and the
steering displays are available, the AC maneuvers
the aircraft in the direction indicated by the roll tabs
on the optical sight to center the vertical needle on
the ADI and/or center roll tabs on the optical sight
(see figure 1-55). When the aircraft ground track is
aligned with the target as indicated by the steering
instruments, the AC should be flying the preplanned
indicated altitude (using either 29.92 Hg or the fore¬
cast target altimeter setting) that will place the air¬
craft at the required altitude AGL and should stabilize
at the release airspeed. The bomb button must be
depressed before the bomb release signal is auto¬
matically supplied to obtain a bomb release. The
bomb button can be released and depressed again
(prior to bomb release) without aborting the offset
bombing run. The WRCS computer supplies the bomb
release signal when the distance to the target, minus
the bomb release range equals zero. Steering infor¬
mation to the target continues to be supplied. Another
bombing run on the same target can be made by flying
the steering instruments and depressing the bomb
button prior to the bomb release point; however, this
method increases the navigation range whichwill
decrease bombing accuracy.

WARNING

VISUAL IP FLY-OVER

When an IP is chosen that will not provide a suitable
radar return, the aircrew must visually identify the
IP, and the aircraft must be flown directly over the
IP. The freeze button and the target insert button
are depressed simultaneously when the aircraft is
directly over the IP. The steering displays are then
available and the AC maneuvers the aircraft accord¬
ingly. If the MAP-PPI radar is in operation, the
cursors will center over, and begin tracking the target.
Prior to the IP, the reset button should be pushed to
ensure that the cursors are at zero-zero; and, the
along-track, cursor control must not be moved prior
to IP. The use of a visual IP will produce greater
bombing accuracy than the use of a radar IP. This is
due to the inherent radar ranging tolerance error of
the radar, and the position error of cursors in estab¬
lishing the exact location of the RIP with respect to
the aircraft. Bombing range error can be further
reduced by choosing an IP that is located as near as
possible to the bomb release point, thereby, reducing
the navigation distance.

TARGET FINDING MODE

The target finding mode (figure 1-55) is provided to
aid the aircrew in navigating from a radar or visual
IP to the target area. The operating procedures and
steering displays are identical to the offset bombing
mode; the target-finding mode does not supply a bomb
release signal. When the aircraft is over the target,
the ADI vertical needle moves off to the side and the
roll tabs on the optical sight will rotate, and the
range indicator counter begins to increase in value
displayed. (The range indicators may not reach
000 MILES.)

The target finding mode is selected by placing the
delivery mode selector knob to TGT FIND and the
navigation computer switches in the NAV mode. The
AN/APQ-109 radar is operated in the MAP-PPI mode
and the optical sight in the A/G mode. The applicable
switches of the ensuing bomb delivery mode may be
preset. The operating altitudes for this mode are
between 50 feet and 60,000 feet AGL. Steering in¬
formation is removed when another delivery mode is
selected or the reset button is pushed.

An alternate use of the target-finding mode is as an
aid to update the ASN-46 navigation computer set
from a radar IP having known coordinates. Set the
north/south and east/west target distance counters
for a real or imaginary target with reference to the
RIP. The target is the location where INS updating
will occur. Position the update switch to SET and
dial the latitude and longitude coordinates of the real
or imaginary target in the navigation computer con¬
trol panel. The pilot uses the cursor controls to
establish a computer fix on the RIP, depresses the
freeze button and the target insert button, and the AC
maneuvers toward the target. Place and hold the INS
update switch in the FIX position. When the BDHI
miles-to-go target counter reads zero and the bearing
needle swings through 90° to the aircraft heading,
release the update switch to the normal position.

1-140

T.O. 1F-4C-34-1-1

WEAPON DELIVERY PANEL!

NORM ON

activate

NORM HCH.D/-TN. NORM X IOO

mm %m

S TGT fIND — PANjr.F

F4E-34-I-320

Figure 1-57

LABS/WRCS BOMBING MODES

The weapon delivery panel and associated circuits
allow the aircrew to energize and use the WRCS tar¬
get find mode simultaneously with any LABS bombing
mode. With the two systems integrated, the WRCS
performs navigation to target functions, and the
selected LABS mode commands the release signal
and delivery flight path. The equipment is provided
essentially for the deployment of nuclear weapons.
However, the equipment and delivery methods will
also apply in certain situations involving non-nuclear
weapons. Hence, the following discussion involves
no specific bomb, but simply assumes that some
bomb(s) - either high or low drag - are aboard the
aircraft.

The AC may select any one of six LABS bombing
modes (including DIRECT) on the delivery mode se¬
lector. Equipment will allow the aircrew to energize
and use the WRCS target find functions in conjunction
with any of these LABS modes, and most specifically
theAN/AJB-7 modes (LADD, LOFT, andO/S). In
this case, the WRCS system is being used to deliver
an AN/AJB-7 activate signal at the proper range from
target and along any ground track projected directly
through the target. The following is a general analy sis
of items that immediately effect aircrew operations.

a. The weapon delivery panel (figure 1 -57) is on the
rear cockpit right console. The panel includes the
activate control switch, the target find switch, and
the range switch. These are lock-toggle switches
that detent laterally into position.

b. The WRCS system is programmed to provide an
extended release range scale to 100,000 feet. This
pertains to the (X100) factor selected on the range
switch, which applies a multiplier of (X100) to what¬
ever is set in the Release Range (Rr) counter.

OPERATION

On the weapon delivery panel (figure 1-57) the pilot
must select HOLD on the target find switch; the HOLD
position selects the WRCS target find mode of operation.

The WRCS computer control panel is set as it nor-
maUy would be for offset bomb operations. The only
difference is that the release range (Rr) counter
must be set with a number representing range from
pullup to burst, which is quoted in the appropriate
LADD ballistics table. Assume that the ballistics
table range (Rb) is quoted at 14,000 feet. This is
the range at which the WRCS system delivers a signal
activating the LADD system. The aircrew should
allow for a small amount of lead-in time at pullup.

The lead-in time compensates for any delay in pilot
reaction time, and allows time for the AN/AJB-7 to
activate into the LADD mode. A feasible lead-in
interval is 1 second, which is placed on the pullup
timer (T^ interval). Therefore, the Rr setting on
the WRCS control panel is

RR = Rb + V A (1-69) Ti,

where Rb is the bombing table range, Va is approach
velocity in knots, and T^ is the desired lead-in time.
For a 1.0 second Ti interval and 550 KTAS approach,
the Rr setting would be 14,900 feet. In the Rr
counter, the pilot would place 149 on the dial and
place the range switch to (X100) on the weapon de¬
livery panel. Finally, the pilot sets the T 2 interval
on the release timer.

Note

*The selection of 1.0 second for a lead-in in¬
terval is only intended as an example here.
Whatever the setting is, it should be as small
as possible since chances of distance error
at the pullup point are increased with longer
Ti intervals. Also, the activate tone is trig¬
gered at the activate point, regardless of
the value placed on the pullup timer. Hence,
the tone may be used both as an activate
signal and a pullup warning signal only if the
pullup timer is set on a low value. Finally,
if Tj is set to zero, the 0.38 second activate
tone occurs directly at the pullup point.

•With the range switch on (X100), the (X10)
factor on the release range counter has no
meaning. The range switch is also functional
in any WRCS modes that require an Rr
setting.

•For the WRCS/LABS modes, any release
advance (Ra) setting on the WRCS panel ad¬
vances the activate point by the amount set
into the counter. Normally, the counter
should be set on zero. However, an Ra set¬
ting may be used to apply a tailwind correction
or to apply a reaction time correction during
the TGT FIND/DIRECT mode.

1-141

T.O. 1F-4C-34-1-1

TGT DISTANCE-EAST

tmm '

TGT DISTANCE- .
NORTH

TIMED

RELEASE

PULLUP

AJB-7

ACTIVATE

WRCS/LADD DELIVERY MODE

* . ft'.

POSITION

UPDATE

TGT

0 POSITION UPDATE

1 . Pilot positions WRCS cursors over IP and de¬
presses FRZ control.

2. Pilot depresses TGT INS control, steering
displayed on HSI, ADI, reticle, and BDHI .AC
steers to null azimuth indicators.

3. Pilot selects ACTIVATE after cursors and steer¬
ing devices complete transition to target.

0 AJB-7 ACTIVATION (Rr)

1 . Activate tone sounds (0.38 sec. beep) and T^
time starts. (Tj =1.0 sec. lead-in time .)

2. ADI pointers centered.

3. Pullup light on.

4. AC starts pullup.

Note

• Bomb button signal may be delivered anytime
during T] + T 2 .

• All other steering instruments (except ADI)
continue WRCS steering.

0 PULLUP

1. ATT] = 0, pullup light off.

2. Reticle light off.

3. Steady tone on.

4. T 2 time starts.

5. ADI pointers:

Horizontal - LADD vertical flight path.

Vertical - yaw/roll error.

6. Bomb button signal must be delivered before

T 2 =0.

0 RELEASE

1 . AT T2 = 0, release occurs.

2. Pullup and reticle light on.

3. Tone off.

4. ADI vertical pointer out of view.

0 RELEASE BOMB BUTTON

1 . Pullup light off.

2. ADI vertical po inter-WRCS steering.

3. ADI Horizontal pointer out of view

4. WRCS steering continues, aircrew may re¬
attack from another direction.

F4E-34-I-321

Figure 1-58

1-142

T.O. 1F-4C-34-1-1

As figure 1-58 indicates, the AC approaches the tar¬
get area using normal target find (or offset bomb)
procedures. The aircrew may select the target as
the IP, use an offset IP, or a visual IP fly-over pro¬
cedure may be used depending on the nature of the
target and weather conditions. Once the target insert
function is performed, the pilot places the activate
switch to ON. Note that if the activate switch is
placed ON before target insert, the LADD system
could energize prematurely. (At target insert, the
WRCS range servos position out to the aircraft range,
from target. If the servos pass through the Rr set¬
ting, the AN/AJB-7 system could activate at that
instant.)

When the aircraft reaches the AN/AJB-7 activation
range (14,900 feet in this case), a signal from the
WRCS triggers the activate tone and starts the pullup
timer (Tj). At this point, the ADI needles switch
into the AJB-7 mode, but the remaining steering
devices continue indicating target find steering. The
activate tone lasts about 1/3 of a second, which means
that the AC has about 2/3 of a second remaining to
react and begin pullup as the T2 interval (release
timer) begins. Notice that the bomb button may be
depressed anytime during the (Tj + T 2 ) interval;
AN/AJB-7 activation occurs automatically and inde¬
pendently of the bomb button when reaching the set
Rr range. However, if the pickle signal is delivered
before reaching the activation range, the AN/AJB-7
sequence will begin immediately. Also, if the AC
inadvertently releases the bomb button during (Ti
+T 2 ) interval, the signal may be reapplied before T 2
run-out without aborting the run. The lock-out relays
are bypassed in the WRCS/AJB-7 modes.

Note

The 1/3-second activate tone mentioned here
is available only in the WRCS/LABS delivery
modes. If the AGM-45 is to be delivered us¬
ing the WRCS/LOFT mode, the activate tone
is not available.

The pullup-to-release portion of the LADD maneuver,
with which the aircrew is familiar, is flown as figure
1-58 indicates. Aircrews may easily equate the pro¬
cedures shown in the figure 1-58 to any other LABS
maneuver. With a LOFT or O/S mode selected for
example, release occurs through the AN/AJB-7 gyro
rather than the release timer. The Rr counter is set
as a function of the desired pullup distance from tar¬
get which would be nearly zero in an O/S mode and
conceivably as much as 30, 000 feet in a LOFT mode.
Also, with the Rr counter set for a known bomb
range, the AC can select DIRECT and apply the re¬
lease signal when the activate tone sounds. In this
case, the aircrew has a DIRECT/TGT FIND release
mode.

After bomb release, the WRCS target find mode con¬
tinues to function and the AC may reattack provided
that the navigation range of the WRCS is not exceeded
(30 nautical miles). If the AC desires, the system is
completely recycled by placing the activate switch to
NORM and by depressing the reset button on the
cursor control panel. The AN/AJB-7 system recy¬
cles automatically at bomb release.

WEAPON DELIVERY PANEL

TGT Find Switch

The HOLD position energizes the target find circuits
along with any LABS mode (including OFF) that the
AC selects.

Range Switch

The range switch is functional in any WRCS mode that
requires an Rr setting. The (X100) position applies
a multiplier of 100 to whatever digit the pilot places
in the Rr counter. In NORM, a factor of 10 is ap¬
plied to the Rr setting.

Activate Switch

Voltage is available for the activate switch as soon
as the target insert button is depressed. Placing the
activate switch to ON provides continuity to activate
circuits in the weapon release computer. These cir¬
cuits close only when the aircraft range from target
becomes equivalent to the set Rr range. This applies
the activate signal to the selected LABS circuits and
the associated indicators. The pilot must avoid a
premature activation by selecting the ON position
only after target insert, and only after the range and
steering devices have transitioned to the target. If
the activate switch is left in NORM, the system is
operating in a pure target find mode where any Rr
setting has no meaning.

AUX ARMAMENT CONTROL PANEL

Gyro Switch

The AC may fast-erect the AN/AJB-7 gyro platform
by selecting the momentary FAST ERECT position on
the gyro switch. This applies an electrical cage sig- '
nal to the gyro caging mechanisms. As the caging
signal is applied, the aircraft should be in level, non¬
accelerating flight. The switch would have application
for example, to correct any noticeable gyro preces¬
sion during the level, constant speed target run-in.

Change 6

1-143

T.O. 1F-4C-34-1-1

JETTISON CONTROLS |F-4E| BEFORE T.O. 1F-4E-556

EMERGENCY JETTISON

The inboard and outboard MAU-12 armament pylons
cannot be jettisoned. The applicable jettison controls
will jettison the MER, TER, or weapon suspended
from the armament pylon. The LAU-34/A launcher
cannot be jettisoned; the jettison controls jettison the
AGM-12B or AGM-45 from the launcher without
motor ignition. The AIM-4D launchers are bolted to
the inboard armament pylon and cannot be jettisoned;
the applicable jettison controls launch the missiles
with motor ignition. When the inflight lockout pins
are installed, the LO, RI and LI UNLOCKED lights on
the DCU-94/A control-monitor illuminate. The RO
UNLOCKED light will not illuminate when the lockout
pin is installed. (Refer to Jettison Procedures, sec¬
tion in.)

EXTERNAL STORES EMERGENCY RELEASE BUTTON

The external stores emergency release button pla¬
carded EXT STORES EMER REL, is a momentary
contact, pushbutton switch used to j ettison the wing
and CL stores (except heat missiles) simultaneously.
This control may be referred to as the panic button.
The button is in the front cockpit on the left vertical
panel. Jettison procedures and the conditions are
contained in section in.

SELECTIVE JETTISON

CENTERLINE STATION JETTISON

The centerline station jettison switch (figure 1-59) is
a cover-guarded switch on the fuel control panel left
console. The switch has two positions: NORM and
JETT. The switch is spring-loaded to NORM. Plac¬
ing the switch to JETT supplies jettison voltage to
the centerline station. Refer to section HI, jettison
procedures.

OUTBOARD WING STATION JETTISON

The wing station jettison switch (figure 1-59) is a
cover-guarded, momentary contact switch, spring
loaded to NORM. The switch is on the fuel control
panel. The switch has two positions: NORM and
JETT. Placing the switch to JETT supplies jettison
voltage to the left and right outboard wing stations.
Refer to section in, jettison procedures.

INBOARD WING STATION (MISSILE
JETTISON SELECTOR)

The missile jettison selector knob (figure 1-59) is a
rotary type pushbutton switch on the missile status
panel. This switch provides selective jettison of the
fuselage missiles and inboard wing stations. The
switch positions are as foUows: OFF, R FWD,

R WING, RAFT, LAFT, L WING, and L FWD. Jet¬
tison voltage is supplied to the left or right inboard
stations by selecting L WING or R WING, and pushing
the jettison button. Refer to section III, jettison pro¬
cedures.

ARMAMENT SAFETY OVERRIDE PANEL

The armament safety override button is a push type
switch consisting of a holding coil and three individual
double pole switches ganged together by a common
plunger shaft and is spring-loaded to OFF. It is above
the left console, in the front cockpit, next to the ejec¬
tion seat. When the override button is depressed,

28v dc is directed to the holding coil from the R 28v
dc bus. This holding coil keeps the override button
depressed and in doing so directs electrical power
from the essential 28v dc bus to emergency jettison
circuits and from the R 28v dc bus to the armament
bus relay. The jettison circuits are placed in an in¬
flight configuration.

WARNING

With the armament override button depressed,
a hazard exists if a centerline station fuel
tank is jettisoned on the take-off roll.

LANDING GEAR CONTROL HANDLE

The landing gear control safety switch is an integral
part of the landing gear control handle and is used to
prevent the inadvertent application of electrical pow¬
er to the armament and jettison circuits. When the
gear handle is UP, this switch directs electrical
power from the R 28v dc bus to the No. 1 miscel¬
laneous relay panel, closing the armament bus relay.
The armament bus relay then supplies electrical
power to the armament circuits. When the gear han¬
dle is DOWN, power is directed through the safety
switch to the armament safety override button hold¬
ing coil; thus, the armament safety override button
remains pulled in when depressed.

LEFT MAIN GEAR SCISSOR SWITCH

The left main gear scissor switch is mounted on the
left main gear strut; it is actuated by a cam on the
bottom of the gear scissor hinge. When the strut ex¬
tends, the scissor links spread and the cam rotates
against the scissor switch, depressing the plunger.
The scissor switch makes contact when the plunger
is depressed. This provides essential 28v dc bus
power to the external stores jettison switch, center-
line tank jettison switch, and the nuclear weapons
jettison switch. The armament safety override but¬
ton bypasses the gear scissor switch and supplies
electrical power to the jettison and release circuits
for ground operation.

NUCLEAR STORES RELEASE AND JETTISON

1-144

Change 6

T.O. 1F-4C-34-1-1

ECM POD JETTISON (STATION 9)

On retrofit and production F-4E aircraft, an ECM
jettison switch (figure 1-59) provides the ECM pod
jettison capability. The two-position cover guarded
switch is placarded JETT and NORM. The ECM pod
may be jettisoned independently from station 9 (other
armament retained) by placing the switch to JETT.
Also, the wing station jettison switch may be used to
jettison stores from the left outboard station without
releasing the ECM pod. When armament is carried
on stations 1 and 9, the ECM jettison switch is by¬
passed and the wing station jettison switch will jetti¬
son armament from both outboard stations. Inadver¬
tent pod release during ground ope ration is inhibited
by the protective circuits discussed earlier in this
text.

MULTI-STATION ECM POD JETTISON

After T.O. 1F-4-821, provisions are added to carry
ECM pods on stations 2 and 8. On F-4E-45 and up;
and all others after T.O. 1F-4E-531, multi station
ECM pod capabilities are added to stations 2, 4, 5,
6 and 8. ECM pods mounted on stations 2, 5, and 8
are jettisoned by following the normal jettison pro¬
cedures for those stations. Refer to figure 1-59 for
switch illustrations. ECM pods on stations 4 and 6
cannot be jettisoned.

Not*

Figure 1-59

release mode. This is accomplished through the
DCU-94/A control monitor and the bomb button. Re¬
fer to section in for procedures. The nuclear release
circuit (DIRECT mode) will not jettison the left out¬
board MER when the MER is shifted aft. The nuclear
jettison circuit (NUCLEAR PUSH TO JETT) will
jettison a left, aft-shifted outboard MER. However,
the right outboard station could also jettison even
though only the left outboard station is selected on
the DCU-94/A.

CAUTION

The nuclear store jettison circuit should not
be used for selective jettison from a partic¬
ular station. The nuclear store jettison but¬
ton (NUCLEAR PUSH TO JETT) should be
used as a last resort, and only when the in¬
advertent jettison from unselected stations
is of little concern. For example, the fuse¬
lage missiles may jettison and both inboard
stations may jettison even though only the
right or left inboard station is selected on the
DCU-94/A. Both outboard stations may
jettison even though only the left outboard
station is selected on the DCU-94/A. When
only the centerline station is selected, only
the centerline station is jettisoned.

ECM pods (except pods on stations 4 and 6)
are jettisoned by depressing the external
stores emergency release button. However,
any decision to jettison ECM pods must be
left to the proper command authority.

MISSILE JETTISON

The jettison circuitry within the firing circuit is con¬
trolled by the missile jettison knob on the missile
status panel. The AC may manually select any one of
the fuselage missiles, either inboard wing station, or
any fuselage missile station for jettison. Before mis¬
siles can be jettisoned, the emergency landing gear
handle must be IN and the weight must be off the land¬
ing gear or the landing gear handle must be UP. For
ground checkout purposes, these interlocks can be
bypassed with the armament safety override button.

RADAR MISSILE JETTISON

With the required interlocks removed, the missile
jettison knob is pushed to jettison the fuselage sta¬
tions. The ejectors used to launch the fuselage mis¬
siles are activated by jettison voltage and not the fire
voltage. These ejectors are gas cartridges which
explode to eject the missile downward from the fuse¬
lage. The jettison circuitry for the two forward fuse¬
lage missiles is interlocked in such a manner that,
if the TK light is illuminated, the missiles cannot be
jettisoned. The AIM-7 missiles are jettisoned with¬
out motor ignition.

Change 6

1-145

T.O. 1F-4C-34-1-1

Note

After T.O. 1F-4-750, the TK light is on be¬
fore and after the Ml 18 or MK 84 bomb is
released when the centerline single bomb
shorting plug is installed. Even though the
TK light is on, the tank aboard relay is not
energized, permitting the two forward AIM-7
missiles to be monitored, launched and jet¬
tisoned.

HEAT MISSILE JETTISON

The jettison knob on the missile status panel allows
the pilot to jettison the AIM-4D and AIM-9 missiles.
The jettison sequence of the AIM-4D is not the same
as the firing sequence: for left wing, L BOTTOM
and after 0.2 sec, L INBOARD; for the right wing,

R INBOARD and after 0.2 sec, R BOTTOM.

The armament pylon cannot be jettisoned. When the
missiles are jettisoned, the rocket motors are ig¬
nited and the missiles are fired ballistically (no
guidance, no self destruct). The normal preparation
of the missiles is not accomplished, therefore, the
warhead fuze in the missile is not armed at launch.
There is a 0,2-second delay between the two AIM-4D
missiles launched on the same station. The flaps
must be UP to jettison the AIM-4D or AIM-9 mis¬
siles. The AIM-4D and AIM-9 launch and jettison
circuit is interlocked with trailing edge flap circuit
to prevent interference during launch. The speed
brakes may sustain damage if they are extended dur¬
ing missile launch or jettison. The landing gear must
be up to jettison the AIM-4D missile. For AIM-9
jettison, the weight must be off the left main landing
gear, i.e., the AIM-9 can be jettisoned if the gear is
down and the aircraft is in flight. For AIM-4D mis¬
siles, the gear up relay is located in the AIM-4D
launcher and prevents AIM-4D launch and jettison
until the gear is up (left main gear door closed).

JETTISON CONTROLS (F-4E) AFTER T.O. 1F-4E-556

Conventional stores jettison controls for these air¬
craft are shown in figure 1-59A. The armament
safety override button, the forward and rear landing
gear handles, the left main gear scissor switch,
AIM-4D gear up relay, and the flaps up relay re¬
main as interlocks in the jettison system. Jettison
controls located on the fuel control panel, and the
ECM jettison control are removed by T.O. 1F-4E-
556.

EXTERNAL STORES EMERGENCY RELEASE
BUTTON

This control (panic button) will jettison simultaneous¬
ly the contents of the four (4) wing armament pylons
and the CL station rack. (This assumes MAU-12 and
BRU-5/A rack cartridges are installed.) Inboard
wing mounted (LI, RI) heat missiles will not jettison,
and fuselage missiles will not jettison.

SELECTIVE JETTISON KNOB

The selective jettison control provides selective jet¬
tisoning of heat and radar missiles, and of wing and
centerline mounted stores. Any store (except nu¬
clear) that can be carried on the aircraft may be
jettisoned through this control.

Radar Missiles

The procedures for jettisoning radar missiles re¬
main the same. The missiles are individually jetti¬
soned by selecting either L FWD, R FWD, L AFT,
or R AFT fuselage stations and actuating the PUSH
TO JETT button. Each fuselage missile jettisons
without motor ignition. If a fuel tank, or a MER is
aboard the CL station, the two forward missiles are

locked out of the jettison circuit and the CL TK
aboard light is on.

Heat Missiles

Heat missiles are jettisoned by selecting the L WING
or R WING (station 2 or 8) position and depressing
PUSH TO JETT. Both missiles on that station are
launched ballistically with a 0.2-second delay be¬
tween missiles.

AGM-65 Missiles

The AGM-65 is jettisoned by using the same proce¬
dures as those for heat missiles. The difference is
that a single missile is jettisoned each time the
JETT button is depressed. The LAU-88/A launcher,
including any missiles aboard, is jettisoned by using
the procedures for wing station stores (below).

Wing And CL Station Jettison

Wing and centerline mounted store jettison circuits
are activated by selecting STORES on the jettison
knob. The STORES position applies power from the
PUSH TO JETT button through the station select
buttons, and on to the cartridge fire circuits of the
wing and CL stations. Therefore with STORES se¬
lected, the AC depresses the required station select
button(s) and depresses the PUSH TO JETT button.
Any single-carried store or MER/TER equipment
with multiple stores are jettisoned. LAU-34/A
launcher mounted stores, such as the AGM-45 mis¬
sile, are ejected with the launcher retained.

1-146

Change 7

T.O. 1F-4C-34-1-1

SUSPENSION EQUIPMENT |F-4E|

BRU-5/A BOMB RACK (AERO-27/A)

The Aero 27/A bomb rack (figure 1-60 sheet 3) is a
self-contained ejector unit mounted within the air¬
craft at centerline station 5. The Aero-27/A rack
has four suspension hooks: two 14 inches apart and
two 30 inches apart. The BRU-5/A rack has only 30-
inch hooks, and arming solenoids in place of the 14-
inch hooks. An ejector piston is in the center of the
rack. When a single weapon is carried, operation of
the rack hooks and the ejector piston is initiated
through the jettison circuit or the nuclear release
circuit by igniting two ejector cartridges. Expanding
gases from the cartridges cause the rack hooks to
open and the ejector piston to push downward on the
weapon. The above procedure is essentially the same
when the rack is configured to accommodate multiple
weapons. However, the forced jettison of a multiple
weapons adapter and MER or a gun pod is inhibited by
installing a force jettison prevention sleeve and pis¬
ton in lieu of the ejector mechanism. The force jet¬
tison prevention sleeve and piston (painted bright
orange for identification), is designed to permit, the
gravity freefall jettison only, and does not affect
normal fire/release of multiple weapons. With the
bomb rack safety pin installed, an electrical safe
switch is opened to prevent the cartridges from fir¬
ing; the pin is removed prior to flight. The MER
cannot be suspended from the bomb rack without the
centerline bomb rack adapter. The weight of the
Aero 27/A bomb rack (51 pounds) is not included in
the basic weight of the aircraft and must be included
in any gross weight computation. The weight of the
BRU-5/A is 45 pounds.

After T.O. 1F-4-750, the two 14-inch suspension
hooks are replaced by two arming solenoids. A cen¬
terline single bomb shorting plug is installed to per¬
mit the release of the MK 84 or Ml 18 GP bomb
through the conventional release circuit. Illumination
of the TK light reveals the installation of the shorting
Plug. S

Note

Even though the TK light is on, the tank
aboard relay is not energized; therefore, the
forward AIM-7 missiles can be monitored,
launched, and jettisoned.

After the bomb is released, the amber station select
light remains on and the TK light also remains on.

The Ml 18 or MK 84 on centerline can be jettisoned
with the external stores jettison button, the center-
line tank jettison switch, the nuclear store jettison
button, and can be released through the DCU-94/A
control monitor.

CENTERLINE BOMB RACK ADAPTER

The centerline bomb rack adapter is attached to the
centerline position to accept the MER assembly. The
adapter is compatible only at the centerline, and at¬
taches directly to the BRU-5/A bomb rack. The
Adapter weighs 55 pounds.

ARMAMENT PYLONS

The inboard and outboard armament pylons (figure
1-60 sheets 3 and 4) are bolted to the wing at stations
1, 2, 8, and 9. The pylons cannot be jettisoned.

Each armament pylon assembly includes the MAU-
12B/A or C/A ejector rack, weapons relay panels, a
power rectifier, and bomb release circuits. The
ejector rack contains two cartridges breeches and
ejector pistons, 14 and 30-inch suspension hooks,
three arming wire solenoids, and a solenoid operated
assembly that electrically locks (safeties) the car¬
tridge fire circuit. When the cartridges detonate,
gas pressure opens the rack hooks and forces the
pistons downward, ejecting the bomb. To compen¬
sate for various bomb eg locations, orifices are in¬
stalled into the rack to control bomb separation
characteristics by varying the forces delivered to
each piston. The ground safety pin provides only a
mechanical lock in the hook linkage for ground safety
purposes.

The inflight safety lockout solenoid electrically iso¬
lates the cartridges by mechanically controlling two
switches that break the cartridge circuit. The lock
must be removed when the MER or TER is aboard by
manually installing the inflight safety lockout pin (or
bolt) in the pylon. The bolt is installed only for non¬
nuclear bomb carriage and must be removed for nu¬
clear carriage. When the bolt is installed, the DCU-
94/A UNLOCK light for that station illuminates con¬
tinuously (except RO station). The arming wire
solenoids are controlled by the position of the arm
nose tail switch.

Change 6

1-146A

arm

CXT STORES
EMERREl

RUSH TO
JETT

STORES

Multi Station Jettison

T.O. 1F-4C-34-1-1

F-4E After T.O. 1F-4E-556

1-146B Change 6

Figure 1-59A

EXCLUDING AIR-TO-AIR MISSILES

4C-34-1-I -(214)

JETTISON STATION
SELECT BUTTONS

EXT STORES
EMERGENCY
RELEASE BUTTON

Selective Stores & Missile Jettison

SELECTIVE JETTISON
CONTROL

T.O. 1F-4C-34-1-1

CERTAIN STORES ARE ALSO
LOADED DIRECTLY ONTO MAU-12
BOMB RACK.

w SAFETY PIN
4815973-1 (DOUGLAS)
Dtwo safety pins required

FOR EACH MER/TER
EJECTOR RACK.

HOMING SAFETY
LIGHT FIN

TER-9

MER-lfl

SAFETY PIN (ELECTRICAL)
4815967-1 (DOUGLAS)

ONE SAFETY PIN REQUIRED
IN EACH MER/TER RACK.

HOMINi

1. LAU-34/A MISSILE LAUNCHER

2. EJECTOR RACK PISTON (2)

3. MAU-12 EJECTOR RACK

4. INFLIGHT SAFETY LOCKOUT PIN (BOLT)

5. (a) TRIPLE EJECTOR RACK ASSEMBLY (TER)

(b) MULTIPLE EJECTOR RACK ASSEMBLY (MER)

6. EJECTOR RACK, MER/TER

7. AGM-12 LAUNCHER BUNDLE (FWD)
AGM-45 LAUNCHER BUNDLE (AFT)

SAFETY

8. JETTISON GUN ACCESS

9. AFT MISSILE RETAINER

10. FWD MISSILE RETAINER

' TER-9A
MER-10 A
(Automatic
Homing)

rocket

11. MISSILE/LAUNCHER CONNECTOR

Figure 1-60 (Sheet 1 of 4)

Chang* 2

1-147

T.O. 1F-4C-34-1-1

OUTBOARD ARMAMENT PYLON F-4E

MOOR MANMA1

niUaii

manmai »rir*n

CAUTION t

ff Kin MUM ft

ViMirn iin* ao*

(HOUND SA.ffM

INC'
1 OltNOXf

tOCM" . Afc'K ' -

ft|TA|N(»S IO 4 0

WITHOUT CARTRIDGES

MOOR N
RtUAll

CAUTION

U (to Wf' ft
ft UNlATCMlP

ckoun; s um m
l»lN MOU

SOlfNCVfl

WITH CARTRIDGES

MAU-12 BOMB RACK
SAFETY PIN 64C13362-3 (AF)
E> ONE REQUIRED IN EACH ARMA
MENT PYLON

F4E-34-I-323-2

Figure 1-60 (Sheet 2 of 4)

CENTERLINE RACK f.4p

T.O. 1F-4C-34-1-1

ROTATED 180

V SAFETY PIN
48X5973-1 (DOUGLAS)

»TWO SAFETY PINS REQUIRED
FOR EACH MER/TER
EJECTOR RACK.

CENTER LINE RACK SAFETY PIN
MDE3254-301

O ONE SAFETY PIN REQUIRED IN THE
BRU-5/A BOMB RACK

1. CENTERLINE EJECTOR RACK (BRU-5/A)

2. ARMING SOLENOIDS (1 AFT 2 FWD)

3. CENTERLINE BOMB RACK ADAPTER

4. MULTIPLE EJECTOR RACK ASSEMBLY (MER)

F4E-34-I-323-3

Figure 1-60 (Sheet 3 of 4)

T.O. 1F-4C-34-1-1

Figure 1-60 (Sheet 4 of 4)

4C—34-1 — 1 —(62—4)

Note

The MAU-12C/A is completely interchange¬
able with the MAU-12B/A armament bomb
rack. The MAU-12C/A is a strenthened
MAU-12B/A.

MULTIPLE EJECTOR RACK (MER)

The multiple ejector rack, used at the outboard wing
stations and the centerline station are: MER-10, and
MER-10A. The MER-10A function differs from the
MER-10 as follows:

a. Only the loaded MER-10A stations receive a re¬
lease pulse regardless of the arm nose tail switch
position.

b. The MER-10A is automatically homed to the first
loaded station in sequence each time power (28vdc
Ess Bus) is applied to the aircraft. The MER-10A
does not have a homing light.

c. The Step switch on the MER-10A is used for
ground checkout operation.

The MER has two suspension lugs mounted 30 inches
apart. The MER consists of six 14-inch ejector units,
12 arming solenoids, the control unit and wire bun¬
dles required to arm, and to release and/or fire
munitions carried. Each ejector rack or point is
identified with a number corresponding to its release
sequence. Outboard wing station MER are rigged 1°
nose down for rockets. The CL MER is rigged
2-l/2 c down for rockets. The centerline MER weight
is 215 pounds, the outboard MER weighs 225 pounds.

1-150

Change 5

T.O. 1F-4C-34-1-1

TRIPLE EJECTOR RACK (TER)

The triple ejector racks used at the inboard wing
stations are the TER-9 and TER-9A. The TER-9A
function differs from the TER-9 as follows:

a. The TER-9A is automatically homed to the first
loaded station in sequence each time power (28v dc
Ess Bus) is applied to the aircraft. The TER-9A
does not have a homing light.

b. The step switch on the TER-9 A is used for
ground checkout operation.

c. Only the loaded TER-9 A stations receive a re¬
lease pulse regardless of the arm nose tail switch
position.

REHOMING MERS AND TERS

A hung bomb can be released, in some cases, after
rehoming the MERs and TERs. Rehoming is ac¬
complished in flight by cycling the weapon selector
knob from BOMBS to RKTS & DISP and back to
BOMBS. This action causes the station stepper
switch in all MER/TERs aboard to move from the
OFF position to the first loaded station in sequence.
The stepper switch will not move if on a loaded sta¬
tion or the MER/TER is empty. (A defective store
aboard sensing switch could cause the MER/TER to
appear empty.) The MER/TER stepper switch OFF
position is obtained only in the BOMBS mode and
after a release pulse has been sent to each of the
loaded stations on the MER or TER. Additional bomb
release pulses will not move the stepper switch from
the OFF position. Selecting RKTS & DISP moves the
stepper switch from the OFF position because there
is no OFF position in the MER/TER with the RKTS
& DISP mode. The MER/TER stepper switch always
steps to the next loaded station and continues to re¬
peat the cycle when the RKTS & DISP mode is used.

Note

• Do not confuse the rehoming procedure per¬
formed by the aircrew with the homing proce¬
dure performed by the load crew. The load
crew will position the STEP-OFF-HOMING
switch on the MER or TER to HOME and ob¬
tain a steady green light. After the load crew
has homed the MERs and TERs, the RKTS &
DISP position will not move the stepper
switch.

• The TER-9A and MER-10A is automatically
homed to the first loaded station, in sequence,
each time power (28v dc Ess Bus) is applied
to the aircraft. The load crew does not home
the MER-10A nor TER-9A.

The following causes of bomb release failure can be
corrected in flight by rehoming the MER's and TER's
provided the MER/TER stepper switch has arrived
at the OFF position.

a. Improper homing of the MER's or TER's.

b. Moisture in the bomb ejector rack breech that
grounds-out the release signal. After the MER's
and TER's are rehomed succeeding release pulses
can (in some cases) generate sufficient heat to evapo¬
rate the moisture in the bomb ejector rack breech.

The following causes for failure of the bomb release
circuit cannot be corrected inflight by rehoming the
MER's and TER’s.

a. Faulty ejector rack cartridges.

b„ Broken or shorted wiring to the ejector rack
cartridges.

c. Faulty relays.

If all the bombs carried do not release, the ejector
racks should be rehomed and release attempted
again. Rehome the MERS and TERS as follows:

a. Weapons selector knob - RKTS & DISP

After the remaining switches are set for bomb re¬
lease, the bomb button is depressed and held for
4 seconds with BOMBS/RIPPLE selected. With the
MER-10/TER-9, if the weapon will not release when
the arm nose tail switch is in an armed position,
rehome and then repeat the BOMBS/RIPPLE release
procedure with the arm nose tail switch in SAFE. If
the station loaded sensor switch has failed in the
station empty position, releasing the weapons SAFE
supplies a release pulse to the loaded stations and
the unloaded station.

Note

• The arm nose tail switch position does not
affect the operation oftheTER-9A, MER-10A
stepper switch; the release pulse is directed
only to the loaded stations.

• If the bombs cannot be released after per¬
forming the preceding procedures, it must
be assured that the ejector rack cartridges
will not fire, or that MER or TER is mal¬
functioning.

Consider the situation where three rocket launchers
are loaded on a TER. The TER stepper switch is on
position No. 1. The TER stepper switch has four po¬
sitions: 1, 2, 3, and OFF. The first loaded point in
sequence is referred to as the home position. As¬
sume that the rocket launchers on points one and two
have been fired-out and the rocket launcher on point
three is full, i.e., no attempt was made to fire the
remaining rocket launcher. (The full launcher must
be released or fired before the empty launchers can
be released.) To release the rocket launchers, the
weapon selector knob is positioned to BOMBS. When
the bomb button is depressed, a pulse is supplied to
release the full rocket launcher on point No. 3. When
the bomb button is released, or the firing pulse is

Change 8

1-151

FORWARD EJECTOR FOOT

MISSILE GONE SWITCH

AFT MISSILE ATTACHMENT

FORWARD MISSILE
HOOK—

UMBILICAL CONNECTOR

AFT EJECTOR FOOT

MOTOR FIRE CONNECTOR

AERO-1A MISSILE LAUNCHER

ROTATED 180°

Figure 1-61 (Sheet 1 of 2)

152

Change 2

S ';.; , v : :■. - ■ •

F4E-34-I* 324-1

AERO-7A LAUNCHER
SAFETY PIN (4)

WEIGHT INCLUDED IN BASIC WEIGHT
OF AIRCRAFT_

AERO-7A MISSILE LAUNCHER

AIM-7 MISSILE

guided missile launchers

AIM-4D LAUNCHERS

INBOARD LAUNCHER.92 LBS

LOWER LAUNCHER.60 LBS

INBOARD ARMAMENT PYLON . . .264 LBS

T.O. 1F-4C-34-1-1

ended, the stepper switch moves to OFF. Succeeding
pulses will not move stepper switch from OFF. To
release the two remaining empty launchers, the
weapons selector knob must be positioned to RKTS
& DISP. Power is now supplied by the stepper switch
to position it to a loaded point; in this case point No. 1.
The AC can now select BOMBS and release the two
empty dispensers.

In this example, the rocket pods are released from
the TER out of normal bomb release sequence, i.e.,
TER station 3, 1, 2. The normal bomb release se¬
quence is TER station 1, 2, 3 (refer to figure 1-44).

I CAUTION I

Rocket pods and CBU dispensers (full and
empty) should be released from the MER/

TER in the normal bomb release sequence
to avoid possible aircraft damage.

There is presently no cockpit indication or procedure
to ensure which MER/TER station is selected for
BOMBS release after RKTS & DISP has been used.
The position of the MER/TER stepper switch is
established by the number of dispensing signals to
the aircraft station and the number of dispensers
(or rocket pods) on that station; i.e., the number of
dispensing pickle signals to a loaded station must be
equal to the number of dispensers loaded on that sta¬
tion (or a multiple of the number of dispensers on
that station) prior to selecting BOMBS to release the
dispensers/rocket pods from the MER/TER.

The release sequence is more likely to be out of se¬
quence when the outboard, inboard, and centerline
aircraft stations are not loaded with the same num¬
ber of dispensers (or rocket pods) and all aircraft
stations are selected for dispensing (RKTS & DISP/
SINGLE). For example: assume a configuration of
4 dispensers on each outboard station and 3 dispens¬
ers on each inboard station and on the centerline
station (17 dispensers total). The inboard and cen¬
terline stations should be deactivated after the third
dispensing pickle (15 dispensers have been emptied).
After the fourth dispensing pickle to the outboard
station, reselect the inboard and centerline aircraft
stations, select BOMBS/RIPPLE, and hold the bomb
button depressed to release the dispensers from the
MER/TER in the normal bomb release sequence.

I AIR-TO-GROUND MISSILE LAUNCHERS

I LAU-34/A LAUNCHER

This assembly must be used to carry and launch the
AGM-12B and AGM-45A missiles. The launcher con¬
tains the electrical circuits and relays which are
responsible for the dispersal of missile pre-heat,
pre-arm, and missile launch voltage. The method of
carriage is illustrated (figure 1-60). The launcher
also contains a cartridge-fired jettison gun assembly
Expanding gas from the detonated cartridges oper¬
ates the assembly and slides the missile rearward,
free of the launcher rails. The missile freefalls in
an inert state.

LAU-88/A LAUNCHER

The LAU -88/A launcher assembly is used to carry
and launch the AGM-65/A (Maverick) missile. Refer
to T.O. 1F-4C-34-1-1A.

AIR-TO-AIR MISSILE LAUNCHERS

AERO-7A LAUNCHER

Four Aero-7A launchers are mounted to the fuselage
so that four AIM-7 missiles are semi-submerged.

The Aero-7A launcher (figure 1-61, sheet 1) has two
ejector pistons which are operated by gas generating
cartridges to eject the missile downward an approxi¬
mate 8 inches before the missile motor is fired. Each
of the forward fuselage stations has a cavity door that
closes after the missile is gone, to smooth the con¬
tour of the fuselage. Each launcher is electrically
and mechanically protected from inadvertent firing
of the ejector cartridges by a safety pin which is
removed prior to flight.

AIM-4D LAUNCHER

An AIM-4D launcher set group (figure 1-61, sheet 2)
consists of the MAU-12B/A armament pylon, the in¬
board AIM-4D launcher, and the bottom (lower) AIM-
ID launcher. The inboard launcher contains all the
electrical and electronic gear for both launchers.

The inboard launcher is bolted to the inboard side of
the MAU-12B/A armament pylon. The bottom launch¬
er is suspended from the MAU-12B/A armament
pylon. Ejector cartridges are not installed ha the
armament pylon. The AIM-4D launchers cannot be
jettisoned. Electrical connections for missile pre¬
launch signals are accomplished through an umbilical
connector from the aircraft power source within the
pylon.

During ground operations, the missile electrical con¬
nector is disconnected to prevent inadvertent firing
and must be connected prior to flight. The AIM-4D
is interlocked with trailing edge flaps to prevent in¬
terference during launch. The speed brakes may
sustain damage if they are extended during missile
launch or jettison.

Note

• After T.O. 11L3-3-5-504, the AIM-4Dlaunch¬
er is modified for AF standard logic and ex¬
tended cooling. After this modification, the
dash number of Inboard Launcher is changed
from -120 to -130. Refer to T.O. 1F-4C-34-
1-1A for additional information.

•After T.O. 11L3-3-5-507, the AIM-4D launcher
is modified for simplified launch procedure.

After this mod, the launcher is marked with
a decal ARM/START LAUNCHER (selecting
missile arm starts missile cooling) and the
dash number of the launcher is changed to
-140. Refer to T.O. 1F-4C-34-1-1A for ad¬
ditional information.

LAU-7A/A LAUNCHER

Refer to T.O. 1F-4C-34-1-1A.

AERO 3B LAUNCHER

Refer to T.O. 1F-4C-34-1-1A.

Change 7

1-155

T.O. 1F-4C-34-1-1

AGM-12 WEAPON SYSTEM [F-4E]

This section describes the AGM-12 guided missile
launching system and associated equipment, and the
cockpit controls and controlling procedures. With
respect to missile control and flight operations, the
missiles are nearly identical. The AGM-12B and
-12C missiles are both ground burst devices, with
the AGM-12C being considerably greater in weight
and explosive yield. The AGM-12E is basically the
same as the AGM-12C, except the -12E missile is
an airburst, anti-personnel device.

Note

In F-4E (71-237) and up, the AGM-12 capa¬
bility is not available. Refer to part 4 of
this section for a description of the AGM
missiles.

MISSION

The AGM-12 missile and associated equipment pro¬
vides the radio-controlled guided missile capability
to enhance the air-to-ground strike mission. With the
AGM-12 system energized, the AC begins an attack
(dive or level) on the target and stabilizes the air¬
plane flight path directly toward the target. The AC
attempts to maintain a constant line-of-sight (LOS)
with the target throughout the missile run. The mis¬
sile fire signal is delivered by depressing the bomb
button (either cockpit), igniting the missile liquid-
fuel engine and the tracking flares. After engine
burn-out (approximately 2.0 seconds) the AC begins
transmitting steering commands to the missile re¬
ceiver. The system transmitter emits the r-f sig¬
nals as the control selector handle is positioned in
combinations of left-right or up-down movements.
Hence, the AC directs the missile flight path in azi¬
muth and elevation, causing the missile (visible
tracking flares) to close on the LOS to the target.

CONFIGURATION AND SUSPENSION

AGM-12B MISSILE

A total of four AGM-12B missiles, one on each wing
station may be carried and launched against tactical
ground targets. The inboard and outboard AGM-12B
suspension equipment for F-4E aircraft is shown in
figure 1-60. Each armament pylon receives the
LAU-34/A missile launcher. The branched wire
bundle from the armament pylon is attached to both
receptacles on the aft end of the launcher. The for¬
ward branch powers AGM-12B functions. (The aft
branch powers AGM-45 missile functions discussed
elsewhere in this section.) In a jettison situation,
only the missile is jettisoned. The LAU-34A remains
with the aircraft.

AGM-12C AND-12E MISSILES

A total of two AGM-12C or -12E missiles may be
carried, one on each inboard station. An AGM-12
relay panel, installed only in the inboard armament
pylon, relays the pre-arm and missile fire/release

signals from the cockpit. Hence, the missile is
loaded directly on the pylon (MAU-12B/A) bomb rack.
In this case, the fire signal ejects the missile from
the rack and the missile engine ignites immediately
after ejection. A discussion of AGM-12C missile
fire and jettison procedures is provided later in this
section.

LAU-34/A LAUNCHER (AGM-12B CARRIAGE)

In general, the launcher (figure 1-60) is responsible
for the proper dispersal of pre-heat, pre-arm, and
missile fire voltage. When the aircraft main bus
system is energized, power is automatically directed
to missile components for warm-up purposes and the
system transmitter receives standby power. Thus,
the system is in a warm-up condition as soon as the
main bus system is energized.

When the AC selects the AGM-12 missile on the
weapon selector switch, relays in the launcher are
energized that unlock the pre-arm and missile fire
circuit. As the AC depresses (and holds) the bomb
button, the missile battery, gyro, pneumatic control
system, and warhead arming circuits are activated.
The missile battery builds up to power and closes a
relay in the launcher - completing the circuit between
the bomb button (depressed) and the liquid engine ig¬
niter. The firing sequence takes approximately 2
seconds. The engine thrust force breaks the shear
pin in the forward retention mechanism (figure
1-60), and the missile is free to launch. As the
missile separates from the aircraft, the umbilical
breakaway connector separates the missile system
function on battery power.

If the missile must be jettisoned, the jettison signal
energizes a cartridge in the launcher jettison gun
assembly. The force of the expanding gas from the
cartridge rotates the aft retention mechanism and
slides the missile rearward, free of the launcher
rail. In this case, the missile f reef alls in an inert
state. Only under the condition of a normal, powered
launch will the warhead become armed.

AIRCRAFT COMPONENTS

TRANSMITTER AND CONTROL SELECTOR
(AN/ARW-77)

With the aircraft bus system energized, 28 volt dc
power is continually applied to the transmitter elec¬
tron tube filaments, crystal heaters, and voltage
regulator. When bomb button voltage is applied at
launch, the ARW-77 transmitter signal is initiated
and an internal timer (in the transmitter) begins a
50 ± 10 second cycle. The timer sustains transmitter
output for the above time period after the AC releases
the bomb button. The output signals from the cockpit
control selector are converted into command pulses
by the transmitter. The transmitter circuits code,
amplify, and apply the commands to the lower UHF

1-156

Change 8

T.O. 1F-4C-34-1-1

antenna. Any one of the 24 command channels may be
used, depending upon the crystal installed in the
transmitter. The transmitter crystal assembly in¬
stalled must match that of the missile receiver.

The control selector (figure 1-64) receives power di¬
rectly from the transmitter and in turn applies com¬
mand output voltages to the transmitter circuit. With
the control handle in the neutral position, the system
continually emits a neutral or reference signal.
Movement of the handle causes signal changes with
respect to the reference signal. The amount of change
is directly proportional to handle displacement. A
further discussion of control handle functions and the
command link (adaptive control) system is provided
in later paragraphs.

MISSILE CONTROL

ADAPTIVE CONTROL SYSTEM

a. Lead Pulse.

b. Variable Pulse Rate Frequency.

c. Auto-Check Command.

d. Memory Command.

When the AC deflects the control handle providing an
input voltage to the transmitter, circuits in the trans¬
mitter develop command pulses by repeatedly con¬
ducting and then deenergizing; applying and removing
voltage for transmitter pulse output. The net result
is that the missile canards momentarily deflect and
then return to neutral as each pulse is applied, con¬
tinuing the pulsating deflections as long as the handle
is displaced. The canards always deflect fully with
each pulse, regardless of the degree of control handle
displacement. As an example, assume that the AC -
having launched a missile - applies an up correction
by moving the handle aft. Further, assume that the
stick is deflected about one-half travel at time To,
and then returned to neutral at time Tj (figure 1-63).
In the figure, off time refers to the time between
pulses when the canards are neutral; on time refers
to pulse duration, which corresponds to canard de¬
flection time.

Since an up correction is necessary, the missile is
low with respect to the LOS and probably going lower
due to the effect of gravity. Also, note that the AGM-
12C/E missile is ejected and not launched, which ap¬
plies another force component to the missile normal
to the LOS. Hence, as the AC moves the stick, the
command must initially apply enough energy to ro¬
tate the missile axis and change its course, and in

some measure account for the time lag in the com¬
mand link system. The lead pulse, that functions
to quicken missile response for the above reasons,
is applied for a longer period that subsequent pulses
as figure 1-63 indicates. The width, or on time, of
the lead pulse is proportional to how rapidly the AC
moves (or accelerates) the stick to the desired posi¬
tion. A rapid movement delivers a lead pulse of
greater duration than that of a gradual movement.
This is in keeping with the natural tendency to cor¬
rect rapidly if the AC notices a large error develop¬
ing. Conversely, the lead pulse function points out
the necessity of using gradual, smooth, control stick
movements in instances where missile steering is
extremely sensitive, or where steering errors are
small.

As long as the control handle is held in the deflected
position, the pulse train continues. After the lead
pulse, subsequent pulses are short at first, increas¬
ing in duration (time) as the stick is held. This
means that the canards are deflected for increasing
periods of time with each pulse. If the AC increases
the amount of handle deflection, the amount of pulses
per unit of time increases, or in other words, the
frequency increases. Hence, the pulse rate frequency
varies proportionally with the amount of handle dis¬
placement. If the handle is displaced to full travel,
the pulse is continuous and canard deflection is con¬
tinuous. This is the same as stating (regarding fig¬
ure 1-63) that of time decreases and on time in¬
creases as handle displacement increases. The idea
is that the AC deflects the handle a specific amount
for an observed error. Then as the missile is ob¬
served to correct toward LOS at a satisfactory rate,
handle deflection may be reduced so that the amount
of error and command pulses delivered approach a
condition of balance. Small random errors are then
corrected by slight, smooth handle movement about
the neutral position.

As the handle is returned to neutral at time Ti, the
automatic check command is delivered. The check
pulse performs very nearly the same function as the
lead pulse, but the situation is reversed. As the
missile corrects and approaches the LOS, a force
must be applied to rotate and align the missile axis
with the LOS - preventing overshoot. Just as the
lead pulse, the pulse duration of the check command
is proportional to the rate of handle movement to
neutral. If the AC notices an overly rapid rate to
closure with the LOS, he would naturally return the
handle to neutral at a rapid rate. Thus, the AC is
able to reduce lateral or vertical acceleration with¬
out handle deflection in the opposite direction.

After control handle voltage is removed, the system
automatically generates small memory commands at
a constant rate. These commands will continue
throughout missile flight unless they are countered by
stick movement in the opposite direction. The fre¬
quency of the memory commands is a function of the
amount and duration of the initial handle displace¬
ment. A small handle deflection held for a long dur¬
ation can develop the same memory as a large han¬
dle deflection held for a short duration. The memory
circuits function to aid in overcoming natural forces

1-157

T.O. 1F-4C-34-1-1

CONTROL HANDLE vs. CANARD DEFLECTION

Figure 1-63

continually acting on the missile. In the example
command cited here, the up memory would serve to
compensate for further gravity drop.

In view of the above, one can visualize the system
when handle movements are made in directions other
than the cardinal ones. If the handle is moved to de¬
liver an up-right command for example, the com¬
mand sequence in figure 1-63 is applied in both up
and right directions simultaneously. The point to be
made is that the AC need not restrict control move¬
ment to cardinal directions only, but may use com¬
binations of the cardinal commands and vary their
magnitude.

CONTROL CONSIDERATIONS

The above discussion treats the system somewhat
ideally for purposes of demonstration. In practice,
there are several more things to consider. The AC
must establish the desired LOS with the wings level,
applying enough forward trim to counteract the ten¬
dency for the nose of the aircraft to rotate as velocity
during the dive increases. Remember that the mis¬
sile gyro is uncaged while the missile is still on the
launcher, and that the gyro establishes a vertical
reference relative to the position of the aircraft.
Thus, if the aircraft is in a 45° left bank at launch
and subsequently rolled level after launch, an up-
command will result in the missile steering up-left.

When firing the liquid engine, the missile is plainly
visible at launch. Engine burnout is identified by a
puff of white smoke. The AC must ensure no com-

1-158

mands are issued until after engine burnout. The
AC will obtain best results if he can avoid the natural
tendency to fix his vision on the missile flares after
launch. Rather, keep the eyes fixed on the target
(or impact point on the target) and view the missile
flares through the peripheral vision. The picture is
similar to the pipper light floating on the wind
screen. This procedure will help maintain a steady
LOS.

In most cases, the missile appears below the target
and to the left or right, depending upon the wing
station used. If the missile is low, the first feasible
command is the up command to initiate the upward
correction, and to help counteract further sink due to
gravity by establishing up memory. At the lower re¬
lease angles, the effect of gravity will be greater. If
the missile is initially high before any commands are
issued, allow gravity to correct the elevation error.

A down command with down memory, plus the effect
of gravity, is sure to result in overshoot before the
LOS. With all systems functioning normally, the
command link system is most sensitive during the
first few seconds after engine burnout. Hence, use
smooth control action to establish a desirable cor¬
rective tretid toward LOS, rather than attempting to
eliminate all sources of error immediately. Missile
steering tendencies will vary, that is, some missiles
will be more sensitive than others. When applying
the initial command, however, all missiles should be
regarded as very sensitive; it is easier to add more
handle displacement than to correct an over-con¬
trolled missile.

T.O. 1F-4C-34-1-1

The AC can get an idea of how much handle deflection
is needed by observing missile trend. To illustrate,
suppose the flares are observed to move from left to
right toward the LOS at a rapid rate. At the instant
the flares move into and coincide with the LOS, the
apparent error is zero, but the error trend remains
very large since the angle between the missile axis
(or flight path) and the LOS is relatively large. In this
case, considerable control movement, with proper
lead, would be necessary to avoid overshoot. How¬
ever, if the missile is considerably wide but gen¬
erally holding position relative to the LOS, the mis¬
sile axis may be considered to be nearly paraEel to
the LOS. In this case, a lesser control deflection
is necessary to divert the missile and the AC uses
smooth control input, varying handle deflection only
to establish a controllable correction rate.

If the missile can be established at a point close (and
parallel) to the LOS early i'n flight, there should
never be any need for large, rapid, control handle
movements. In fact, during this early phase of mis¬
sile flight, the AC will usually have to use conscious
effort to avoid overcontrol. With the adaptive sys¬
tem, a small degree of handle displacement held for
a longer time produces the same effect as a full
deflection for a very short interval. The former is
by far the more desirable, however, since the trend
of missile correction is more easily judged. The
confusing effect of gravity must be kept in mind, and
possibly used to advantage. As dive angle increases
that component of gravity that tends to pull the mis¬
sile down from the LOS becomes less. However, if
the missile steers slightly high, up memory will
probably not be sufficient to continuously hold the
missile high and gravity may be used to make the
necessary correction. The AC must avoid anticipat¬
ing the impact, and continually fly the missile until
impact is observed.

Roll Reference Shift

The description of the AGM-12 gyro system (part 4)
points out that at supersonic velocity, the missile
roll rate is an average 500° per second. Further,
the pickoff brushes in the gyro are biased 50° to
compensate for 0.1 second time lag in the command
link system. As the missile decelerates, however,
and approaches the transonic region (Mach 1.1 to 0.9),
the lift force at the wing tips increases rapidly and
causes a rapid increase in roll rate. Missile roll
can increase to an approximate maximum rate of
1000° per second. Thus, maximum shift becomes
approximately 100°, which means that the original 50°
bias no longer compensates for the command lag and
missile response would occur 50° counterclockwise
from the desired response. It is difficult to predict
the point at which roll reference shift begins since
one must consider factors such as launch angle,
launch velocity, and individual control technique
which directly effects the rate of missile decelera¬
tion. If the technique of steering the missile along
the LOS is executed properly, the buildup rate of
roll reference is very slow and actual observance
of the shift phenomenon is impossible.

A rule-of-thumb method has been devised that -
knowing a desired time of flight (Tf) - may be used
to determine launch altitude (AGL) for a specific dive
angle. The method makes use of a factor which cor¬
responds to a specific Tf as follows:

Factor

T f

0.3

10 sec.

0.4

15 sec.

0.5

20 sec.

0.6

25 sec.

0.7

30 sec.

For example, assume the AC begins the dive on tar¬
get, establishes LOS, and observes the dive angle to
be 35°. If the 20 sec. Tf is planned, the factor of 0.5
is applied (above) so that launch altitude (AGL) is:

0.5 x 35° dive = 17.5 thousand feet AGL.

If target altitude is 1500 feet MSL, indicated launch
altitude becomes:

17.5 + 1.5 = 19.0 thousand feet.

The above method is accurate (AGM-12B missiles)
within ± 2 seconds for dive angles within 15° and 45°,
and launch airspeeds between 300 and 600 KTAS.

OFFSET DELIVERIES

All previous considerations stated apply to offset de¬
liveries. In this delivery, the LOS continually ro¬
tates. For example, if the target is approximately
10° right at launch, it may move to a relative posi¬
tion of 40° right at impact. In view of the shift phe¬
nomenon discussed, the target must always be offset
to the right. In a shift environment, a right com¬
mand would result in an up-right response, a rela¬
tively easy situation to control. A left command,
however, would result in a down-left response,
which is nearly impossible to control in an offset
mode. In any delivery situation, the rate of LOS ro¬
tation can be reduced by reducing airspeed to as low
a rate as the situation permits.

COCKPIT CONTROLS

The F-4E aircraft pedestal panel configuration is
shown in figure 1-43. The following discussion per¬
tains to the deployment of AGM-12B, -12C, and
-12E missiles.

WEAPON SELECTOR KNOB

On the pedestal panel, the AC selects the AGM-12
position with either missile aboard. This selects the
required firing system by closing relays in the
launcher (AGM-12B) or in the inboard pylon AGM-
12C relay panel. In this function, the intervalometer
is placed in a singles output mode so that missile fire
voltage is directed only to the selected wing station.
Finally, selecting AGM-12 closes one portion of the
transmitter-activate circuit; the transmitter may be
tested after energizing the master arm switch.

1-159

T.O. 1F-4C-34-1-1

AGM-12 CONTROL SELECTOR } -

-—-IF-4E

F4E-34-I-326

Figure 1-64

MASTER ARM SWITCH

Placing the master arm switch to ARM energizes the
bomb button transfer relays, which will direct bomb
button voltage into the conventional weapons circuits.
The transfer relays will not energize, however, if
any of the special weapons release relays (5) are
energized. Thus, either the DCU-94/A master re¬
lease lock, of the station select (all 5), or the con¬
sent switch must be off. Selecting ARM immediately
closes the bomb button/transmitter-activate circuit.
If, at this point, the AC depresses the bomb button,
the system transmitter begins the 50 ± 10 second
cycle. Hence, this method may be used to test (while
airborne) the aircraft portion of the command link
system. The station select buttons must remain off
to avoid firing the armament.

Note

• For transmitter ground test purposes, a
Gam-Aux switch is located in the nose wheel
well.

• To perform any AGM-12 functions that are
executed through the bomb button, the de¬
livery mode selector must be positioned on
DIRECT.

• The Good Guidance Monitor (GGM) performs
a safing function in the AGM-12E fuzing sys¬
tem (refer to section 4 of T.O. 1F-4C-34-1-
1A). In F-4E aircraft, the function is acti¬
vated during missile flight by pulling the
armament power circuit breaker (6B), No. 1
panel in the rear cockpit. Pulling this circuit
breaker deenergizes AN/ARW-77 transmitter
output.

STATION SELECT BUTTONS

These controls are pushbutton switches containing
green and amber indicator lights inside the button
housing. The green light simply indicates that a
specific button has been depressed. Therefore, if
one or more buttons are on, the green lights will il¬
luminate immediately as the a-c bus system is ener¬
gized. Both lights are tested through the test control
on the right console.

With a specific button depressed, the light indicates:

1. That the pylon wire bundles are properly in¬
stalled for the specific station selected. In the
case of the AGM-12B, the light indicates that
the LAU-34/A launcher bundle is plugged into
the proper pylon receptacle. With the AGM-
12C or 12E aboard, the light indicates that the
AGM-12 relay panel is properly connected into
the aircraft/AGM-12 circuits.

2. That the station select relay is closed, which
connects bomb button output to missile launch
circuits.

3. That the master arm switch is positioned to
ARM, which closes another interlock in the
bomb button circuit.

1. Left OUTBD (LO)

2. Left INBD (LI)

3. CL

4. Right INBD (RI)

5. Right OUTBD (RO)

In order to fire an AGM-12B missile from the RO
station, all of the other station select switches must
be off.' To fire the LI station missile, only the LO
station must be off. The CL button is included even
though this station is not AGM-12 capable. This
merely points out that it is impractical to energize
all stations at once with several AGM-12 missiles
aboard. Rather than commit the above order to
memory, the AC may simply select one station at a
time, and after firing the selected missile, place
that station off before selecting the next.

JETTISON CONTROLS

The controls by which the AGM-12 missile may be
jettisoned are shown in figure 1-59. The AGM-12C
and -12E missile is jettisoned (ejected) directly from
the MAU-12 rack in the armament pylon. The AGM-
12B missile is jettisoned (kicked) rearward by the
LAU-34/A launcher jettison gun assembly.

1-160

T.O. 1F-4C-34-1-1

COMBAT SUPPORT EQUIPMENT

OPTICAL SIGHT CAMERA, KB-25/A

After T.O. 1F-4E-558, the KB-25/A 16mm gunsight
camera is installed just above the optical display
unit (ODU) and along the centerline of the sight com¬
bining glass (figure 1-64A). The camera is operated
to provide film documentation of the sight picture
during munition delivery modes in which the optical
sight is in the primary aiming reference. The cam¬
era may be operated with or without the expenditure
of munitions by using controls available in either
cockpit.

The KB-25/A system consists of the camera body,
lens assembly, and a 100-ft capacity magazine or a
dummy magazine. The lens covers a field of view
of 8.25° in azimuth and 16.0° in elevation. The ele¬
vation limits are +3.0° to -13.0° with respect to
zero bo resight line. In addition to the KB-2 5/A cam¬
era, the following aircraft equipment is added or
changed to comprise the complete camera system.

a. A new instrument panel center glare shield is
installed to accept the camera.

b. Gun camera pre-run switches are added to both
cockpits. The aft switch is mounted on the lower left
edge of the main instrument panel. The forward
switch is beneath the canopy sill on the left side.

c. The forward cockpit stick grip is replaced with a
new grip containing a two position trigger switch.

The first detent is referenced here as trigger 1; the
second detent is trigger 2.

CAMERA OPERATION AND CONTROLS

The camera receives motor power as soon as the
aircraft bus system is operating. The only control
that operates the camera on the ground is the camera
run (test) button on the right side of the camera.

With the button depressed, the AC can watch the
motor knob and check that the motor is running (fig¬
ure 1-64A). This may be accomplished immediately
with no other control procedure necessary.

The remaining controls on the camera body are the
frames per second (FPS) switch, the overrun dial,
and the aperture control shown in figure 1-64A. The
FPS switch controls film speed; either 24 or 48
frames per second. The overrun dial is set on the
required time period the camera is to run after the

AC releases the trigger or bomb button. (The over¬
run function does not operate unless trigger 2 or the
bomb button is used to operate the camera.)

Bomb Button

For the bomb button (either cockpit) to operate the
camera, the delivery mode selector must be on
DIRECT, DIVE TOSS, or DIVE LAY. The bomb but¬
ton signal energizes the camera motor, the overrun
period, and the event marker. The event marker
appears on the film to mark the application of the
weapon launch/fire signal.

Trigger Switch (Trigger 1 and 2)

The trigger 1 position of the trigger switch operates
only the camera motor; the event marker and over¬
run period do not operate in trigger 1. The trigger
2 position runs the camera, and energizes the mark¬
er and overrun time. If armament is to be expended,
only the trigger 2 position applies the fire/launch
signal, provided the remaining weapons controls are
energized.

On aircraft modified by T.O. 1F-4E-558,
continuous gunsight camera operation after
takeoff and before initiation of any camera
operational mode indicates a possible mal¬
function in the armament circuit that could
cause premature firing of the gun, air to
air missiles, or prevent the normal release
of the MK 1 Mod 0 Walleye. All trigger func¬
tion armament switches should remain OFF/
SAFE.

If the AGM-45/62 position is selected on the pedestal
for walleye operations, the trigger is locked out and
only the bomb button operates the camera.

Gun Camera (Pre-Run) Switches

The camera may be operated through the gun camera
(pre-run) switches added to each cockpit. With either
switch in the ON position the camera runs continu¬
ously until the switch is placed OFF, or until the
bomb button or trigger 2 is applied.

Change 5

1-160A

OPTICAL SIGHT CAMERA, KB-25/A

FRONT COCKPIT

tOCK.

SMf R

RFTIClFDtPR

REAR COCKPIT

c*oi

(f OFF

GUN CAMRjfl

OVERRUN SW
0, 3, 10 OR 20 SEC,

CAMERA RUN
(TEST BUTTON)

APPERTURE

CONTROL

COVERAGE

LENS

COVERAGE

MOTOR

KNOB

FRAMES/SEC
SWITCH —

FRAMES/
SEC. SW

MOTOR KNOB

100 FOOT
MAGAZINE

T.O. 1F-4C-34-1-1

PART 4 DESCRIPTION

F-4C U E

TABLE OF CONTENTS

COMBAT WEAPONS
AGM-45 Missile
Refer to T.O. 1F-4C-34-1-1-1
AIM-4D Missile
Refer to T.O. 1F-4C-34-1-1-1
AIM-7D, -7E, -7E2 Missiles
Refer to T.O. 1F-4C-34-1-1-1
AIM-9B, -9E Missile System
Refer to T.O. 1F-4C-34-1-1-1

Gun Pods.1-162

20mm Ammunition.1-167

Ml 17 General Purpose (GP) Bomb . . . 1-169

M117R (Retarded) GP Bomb.1-170

M117D Destructor.1-170

Ml 18 General Purpose (GP) Bomb ... 1-171

MC-1 Gas Bomb.1-172

M129E1, E2 Leaflet Bomb.1-173

MK I Mod 0 Guided Weapon
Refer to T.O. 1F-4C-34-1-1A

MK 82 (Snakeye I) GP Bomb.1-174

MK 36 Destructor.1-174

MK 82. MK 83 and MK 84 LDGP Bombs. 1-174
BLU-l/B, B/B, C/B Fire Bombs . . . 1-177

BLU-27/B, A/B Fire Bombs.1-178

BLU-52/B, A/B Chemical Bombs ... 1-178
Fire/Chemical Bomb Fin Assemblies . . 1-178
BLU-76/B General Purpose Bomb . . . 1-178A

SUU-7 Dispensers.1-179

SUIJ-30 Dispensers.1-185

SUU-13 Dispensers.1-186A

SUU-36 Dispensers.1-190

SUU-38 Dispensers.1-190

M36E2 Incendiary Cluster Bomb .... 1-190
MK 20 Mod 2 And Mod 3 (Rockeye II)

Cluster Bomb.1-191

Rockeye n (MK 20 Mod 2) Cluster Bomb. 1-191

SUU-25A/A Flare Dispenser.1-191

SUU-25B/A Flare Dispenser.1-194A

SUU-25C/A Flare Dispenser.1-194A

LUU-l/B, -5/B, -6/B Target Marker

Flare.1-194A

LUU-2/B Flare.1-196

MK 24 Mod 4 Flare.1-196

MLU-32/B99 Flare (Briteye).1-197

SUU-42/A Flare Dispenser.1-198

LAU-3/A Rocket Launcher.1-199

LAU-32, -59, -68 Rocket Launchers . . 1-200

2.75-inch Folding Fin Aircraft Rocket. . 1-201

2.75-inch Rocket Warheads.1-202

2.75-inch Rocket Fuzes.1-205

A/B 45Y-1, Y-2, Y-4 Spray Tanks . . . 1-206

TMU-28/B Spray Tank.1-208

PAU-7/A Spray Tank.1-208

AGM-12B, -12C, -12E Missiles
(Also refer to T.O. 1F-4C-34-1-1-1) . 1-210
Laser Guided Bombs (MK 82, MK 84,

M118).1-213

BOMB FUZES

Classification of Bomb Fuzes.1-217

Safety Features.1-219

Arming Wire Lanyard Routing.1-219

Nose Fuzes.1-224

MK339 Mod 0 Mechanical Time Nose

Fuze.1 -224

M904E1/E2/E3 Nose Fuze.1-224

AN-M147A1 Mechanical Time Fuze. . . 1-225

M907 Mechanical Time Fuze.1-225

FMU-26B/B Fuzes.1-227

FMU-72/B Long Delay Fuze.1-232

FMU-56/B Proximity Fuze. 1-234B

FMU-56A/B Proximity Fuze.1-235

FMU-56B/B Proximity Fuze.1-237

FMU-81/B Short Delay Fuze.1-234

Tail Fuzes.1-237

M905 Tail Fuze.1-237

FMU-54/B Tail Fuze.1-241

FMU-54A/B Tail Fuze,MK-43 Target

Detecting Device.1-242

Fuze Extenders. 1-242B

TRAINING WEAPONS AND EQUIPMENT
SUU-20/A, A/A, B/A Bomb and

Rocket Dispensers.1-243

SUU-21/A Bomb Dispenser..1-246

Practice Bombs.1-248

Umbilical Test Set (UTS) AN/AWM-19 . 1-250

Radar Scope Camera.1-250

TDU-ll/B Target Rocket (5-Inch

HVAR).1-253

AJM-4D Training Missile.1-252

TDD-22A/B Tow Target.1-255

Tow System (RMU-8/A).1-255

A/A 37U-15 Tow Target System .... 1-262

COMBAT SUPPORT EQUIPMENT

KB-18A Strike Camera System.1-264

Combat Documentation Motion Picture

System.1-265

Radar Transponder SST-181X.1-265

CTU-1/A Supply Container.1-266

KY-28 SPEECH SECURITY UNIT
(T.O. 1F-4C-34-1-1-2)
AN/APX-76A INTERROGATOR SET
(F-4C/D) (T.O. 1F-4C-34-1-1-1)
ECM PODS (T.O. 1F-4C-34-1-1-1)
QRC-160-1 (ALQ-71)

QRC-160-2 (ALQ-72)

QRC-160-8 (ALQ-87)

QRC-335A (ALQ-101)
AN/ALQ-71 (V)-3
QRC-335A(V)-3

Change 8

1-161

T.O. 1F-4C-34-1-1

COMBAT WEAPONS

The non-nuclear weapons and associated fuzing com¬
ponents are described and illustrated in the following
pages. Bombing tables (or ballistics tables) are
available for these munitions in T.O. 1F-4C-34-1-2
| and -2A. Only limited information with respect to
weight, drag, and dimensions of these munitions are
shown in this manual. Total aircraft drag and total
gross weight, which are important factors for mis¬
sion planning, must be determined by referencing
T.O. 1F-4C-1-1 flight manual performance data.

For example, to compute the total drag index, mul¬
tiply the number of bombs aboard by the bomb drag
index, and add the suspension equipment drag (shown
in the flight manual) for each loaded station. The
normal release sequence for F-4C/D/E aircraft are
shown in their respective parts of this section. A

I Bomb/Fuze compatability chart is provided; refer
to Bomb Fuzes, this part.

GUN PODS

SUU-16/A GUN POD

The SUU-16/A gun pod (figure 1-66) contains the
M61A1 20mm gun, a RAT (ram air turbine) drive as¬
sembly, an ammunition feed assembly, an electrical
control package, and the ammunition drum. The
M61A1 gun has six barrels that rotate. Each barrel
fires once per revolution to fire a total of 6000 rounds
per minute (100 rounds per second) when the gun is
rotating at 1000 rpm. The muzzle velocity is 3380
feet per second. The M61A1 gun fires electrically
primed, steel case, 20mm ammunition, M50 series,
type TP (ball, used for target practice), HEI (high
explosive incendiary) and API (armor piercing incen¬
diary). The gun pod has an ammunition capacity of
1200 rounds, of which approximately 50 to 70 rounds
are unusable.

I CAUTION {

* The usable ammunition in the pod can be com¬
pletely fired out with a single burst, or fired
in short bursts; however, to reduce possible
gun damage and prolong gun life, a single
burst should not exceed three seconds.

* Firing bursts in the AUTO CLEAR mode with
less than a 2-second interval will cause ex¬
tensive damage to the gun.

to preclude the ejection of live rounds from the gun
and to provide immediate gun firing when the trigger
is pulled.

The RAT (ram air turbine), mid-way along the right
side of the gun pod, is extended into the airstream
when electrical power is applied to the gun pod.
Electrical power is received from the aircraft,
converted within the gun pod, and used to fire the
cartridge and operate the clutch/brake actuator sole¬
noid. Mechanical power to rotate the gun is received
from the RAT; therefore, the RAT directly controls
the rate of fire. The RAT rotates at a constant speed
to provide mechanical power to drive the gun and the
ammunition feed system. The speed of the RAT is
maintained at 12,000 ± 600 rpm by a mechanical gov¬
ernor. Any change in rpm will cause the governor to
change the turbine blade pitch accordingly to main¬
tain a constant speed. A minimum airspeed of 330
knots CAS (Mach 0.5) is required to drive the system
at a steady rate of 12,000 rpm. The gun can fire at
lower than 330 knots CAS; however, the rate of fire
will diminish. The clutch assembly transmits the
power developed by the RAT to the ammunition feed
system and the gun. When the trigger switch is ac¬
tuated, a drive clutch is engaged by a solenoid to
place a gear train in action which reduces the 12,000
rpm to rotate the gun at 1000 rpm, which causes
6000 rounds per minute to be fired from the gun.

During a non-firing condition, the RAT free-wheels
while the gun and feed system are held fixed by the
brake band. When the fire command is given, a
solenoid engages the clutch band against a drum and
releases the brake band to allow the RAT to drive
the system. The ammunition drum stores the major
portion of the ammunition.

During firing operation, the ammunition drum dis¬
charges the ammunition into an endless conveyor
unit which picks up each cartridge and delivers it to
the gun. The cartridges are placed into the gun, as
it rotates from the lower right side, where a cam-
operated sliding bolt assembly picks up the car¬
tridge and carries it forward and locks it in the
breech (or firing position). The cai'tridge is fired
as it passes an electrical contact, and the empty
case is extracted as the gun rotates toward the lower
left side. The empty case (or a dud cartridge) is
extracted from the breech and ejected from the lower
left side of the pod by the case ejector with sufficient
velocity to clear the aircraft.

The gun lias two operating modes that can be se¬
lected inflight: AUTO-CLEAR and NON-CLEAR.

The purpose of the .auto-clear mode is to remove
live rounds from the firing position at the completion
of each burst. The purpose of the non-clear mode is

At the end of each burst, in the AUTO-CLEAR mode,
an automatic clearing function is initiated which pre¬
vents the bolts from carrying the cartridges forward
into their breech position during gun deceleration.

1-162

Change 7

T.O. 1F-4C-34-1-1

to clear the gun of live rounds. A live round re¬
maining in the breech after a long burst in the non-
clear mode could cook off if the gun is hot. This will
not cause the gun to malfunction. When a gun mal¬
function occurs, the cause will most often be the
jamming of the feed system. Another type of mal¬
function that might occur, is the jamming of the bolt
assembly operation in the auto-clear mode; the non-
clear mode is not susceptible to this type of malfunc¬
tion.

CAUTION j

Firing bursts in the AUTO-CLEAR mode
with less than a 2-second interval between
bursts will cause extensive damage to the
gun.

Complete fire-out of all ammunition is not possible;
approximately 50 rounds must remain in the feed sys¬
tem to maintain control of the flexible feed chute.

A last-round switch is in the ammunition drum to
stop the feed system before the last round in the
ammunition drum reaches the feed system. Firing
voltage is removed by the last round switch as if the
trigger switch were released, and the auto-clear
clearing action is initiated regardless of the mode
selected; all cartridges are removedfrom the breech.

The M61A1 gun can develop 3800 pounds of reverse
thrust when firing at its maximum rate. Since the
guns are mounted below the aircraft center of
gravity, the reverse thrust of the centerline gun will
cause the pipper to rotate downward approximately
5 mils. The two outboard guns will also cause a
downward rotation and to a greater degree; approxi¬
mately 8 mils. One outboard gun can be safely fired;
however, the reverse thrust will cause the pipper to
rotate in azimuth (yaw approximately 8 mils) toward
the operating gun. For short bursts of less than 1
second, the reverse thrust of the guns will cause
negligible movement of the pipper and, consequently,
the shot pattern. The AC should anticipate the effect
of reverse thrust and aim at the top of the target,
or to the side of the target.

r m

! CAUTION

A maximum burst time of 3 seconds should
be observed to reduce possible gun damage.

Note

If the gun control switches and the missile
control switches are positioned for firing,
only the guns fire when the trigger switch
is actuated. The position of the missile arm
switch has no effect on the gun firing circuits.

The guns can be fired with flaps down and/or
speed brakes deployed.

* F-4D-28 and up, the forward fuselage AIM-7
missiles can be launched when the gun pod is
mounted on the centerline station.

SUU-23/A GUN POD

The SUU-23/A gun pod is similar to the SUU-16/A
gun pod, except it contains the XM130 gun and does
not have a ram air turbine (RAT) drive system. In¬
stead, it has an internal electric inertia start motor
which accelerates the gun. With the gun selected,
the inertial start motor begins to develop operating
speed when the master arm switch in placed to ARM.
On production F-4D/E block 37 and up and on all
other F-4D/E aircraft with prestart retrofit, the
inertia motor in the SUU-23/A starts running when
the station is selected, regardless of the position of
the master arm switch or the weapon selector. A
jumper bundle is added to the armament stations to
provide selective pre-start capability. Pre-starting
of the inertia motor through the station selector but¬
tons eliminates the 20 to 30 second delay in firing
after master arm.

The station select buttons immediately ener¬
gize the SUU-23 gun pod pre-start circuits
and start the gun inertial motor. To avoid
inertial motor burn-out, avoid selecting the
stations during ground operations or any op¬
erations not directly involving the gun pod.

This also applies to SUU-23 pods mounted on
INBD stations (2 and 8) after T.O. 1F-4D-
558.

When the trigger is pulled, the inertia starter ac¬
celerates the gun to 5400 shots per minute. At 5400
shots per minute, the inertia starter disengages and
a gas drive system extracts gun gas from four of
the six barrels to further accelerate the gun to the
maximum firing rate of 6000 shots per minute. With
the motor operating at duty speed, maximum gun
firing rate is obtained 0.2 to 0.4 seconds after the
trigger is pulled.

The gas drive system sustains the driving rate of
the gun and linkless feed system. The electric
inertia start motor disengages, but continues to
run. If a malfunction occurs (such as misfire of
four or more consecutive rounds), or if the driving
rate falls below 900 rpm (5400 shots per minute),
the electric inertia start motor engages to achieve
firing rate, and again disengages. All data per¬
taining to the SUU-16/A gun pod is applicable to the
SUU-23/A gun pod except when noted.

HARMONIZATION

Figure 1-67 illustrates the convergent method of gun
pod harmonization. The convergent method provides
maximum projectile density at the harmonization
range (2250 feet). Further information is provided
in section IV, Supplementary Data. Figure 1-67 also
shows the position of the optical sight range bar at
the 1000 through 4000 foot range indicating positions.
The range bar is available only in the lead compute
operating mode with radar lockon.

Change 3

1-165

HARMONIZATION RANGE

1000 FT
MIN

RANGE

2250 FT
HARMO
RANGE

—

8 MIL CONE —

HARMONIZATION

RANGE

ZERO

1-166

Change 3

T.O. 1F-4C-34-1-1

WINGSPAN VS. TARGET RANGE

Another device for quickly estimating the air-to-air
target range involves the 25- and 50-mil reticle cir¬
cles and the known wingspan of the target. The AC
may find the device useful if radar lockon cannot be

I obtained (range bar not available). Before T.O. 1F-
4E-556 and without lockon the sight provides lead for
a constant 1500 foot range. After T.O. 1F-4E-556,
the lead range without lockon or with CAGE applied
during lockon is 1000 feet. As an example, the F-4
wingspan is 38 feet. At 1500 feet range, the F-4
would diametrically fill the 25-mil reticle ring.

(1000) 38 ft. WS = 25 Mils Dia. (Approx)

1500 ft. Rng.

The plot in figure 1-68 provides values of mils diam¬
eter as a function of wingspan and target range.

| OPTICAL SIGHT VS WING SPAN~~

Figure 1-68

20mm AMMUNITION

The components that make up a complete round or
cartridge used in the M61A1 gun are: a brass car¬
tridge case, an electric primer, propellant powder,
and the projectile. The complete cartridge is approx¬
imately 6-5/8 inches long and weighs approximately
1/2 pound (Ball, 0.5621; API, 0.5696; and HE I,

0.5664 pound). The projectile is fired when an elec¬
trical pulse is applied to the primer. The resulting
flame passes through a gas vent leading to the pro¬
pellant chamber which ignites the propellant in the
cartridge case. As the propellant burns, it forms a
gas which forces the projectile through the gun
barrel.

The only significant difference between the three
types of ammunition is in the projectile. Located at

20mm TARGET PRACTICE (TP) and
TARGET PRACTICE-TRACER (TP-TJ

P R0 P EL1 ANT;—

lisi

v/v'k

CASE VENT

Hi seal

ELECTRIC PRIMER i

DISK

CUP-

CUP SUPPORT

CHARGE

BUTTON

electrical primer

4C—34—1 — 1 —(70)

Figure 1-69

the rear of all projectiles is a band of soft metal
that seats in the grooves of the gun barrel. The
grooves in the barrel are twisted such that the pro¬
jectile receives a rotating motion as it travels
through and leaves the gun barrel. This rotation is
induced to provide stability in flight. The soft band
also serves to prevent the propelling gas from
escaping past the projectile.

Note

The 20mm Dummy color code may be either
bronze or shades of grey or tan. The case
will be steel or plastic. Dummy ammo is
used to check out the gun system and for load¬
ing instructions.

20mm Target Practice

The 20mm target practice cartridge (TP), figure
1-69 is ball ammunition. The body of the projectile
is made of steel. The projectile is hollow and does
not contain a filler.

Change 6

1-167

ALUMINUM

CENTRIFUGAL SPRING

FIRING PIN

COVER

DETONATOR

ASSEMBLY

BODY

20mm ARMOR PIERCING
INCENDIARY (API)

■ - •- : .

PROPELLANT

20MM

'Marking in Red)

CASE VENT

v :

ELECTRIC

...

DETONATOR
ROTOR ASSEMBLY

a a ;..

CASE VENT

ELECTRIC

HEIFUZE

Figure 1-70

20mm High Explosive Incendiary

The primary use of the 20mm High Explosive Incen¬
diary (HEI) Cartridge (figure 1-71) containing an
HE1 projectile, is against aircraft and light material
targets because the projectile explodes with an in¬
cendiary effect after it has penetrated the surface of
its target. HEI projectiles require a fuze to com-
plete the explosive train (figure 1-71). The fuze will
not function unless the detonator is in line with Hie
firing pin. The mechanisms are arranged so that the
fuze is boresafe (detonator safe). A boresafe fuze is

Figure 1-71

one in which the explosive train is interrupted while
the projectile is still in the bore, or barrel of the
gun; premature action of the bursting charge is pre¬
vented if the more sensitive element (the detonator)
functions.

The fuze has a delayed arming distance of 20 to 35
feet from the muzzle of the gun. Prior to firing HEI
projectiles, the rotor containing the detonator (which
is out of line with the firing pin) and the firing pin
are locked in position by a rotor safety spring. Cen¬
trifugal force, created by the projectile spin, allows
the detonator to align with the firing pin and the
booster; the projectile is now armed. Upon impact,
the projectile presses into its target, crushing the
nose of the fuze and forcing the firing pin against the
detonator. The booster, initiated by the detonator,
causes the projectile to explode.

1-168

T.O. 1F-4C-34-1-1

WEIGHT FULL . 820 Pounds

LENGTH .7 Ft., 3.4 Inches

DIAMETER.16.0 Inches

FINSPAN . 22.38 Inches

SUSPENSION

LUG DISTANCE:..14.0 Inches

FLIGHT LIMITS :.Refer to Flight Manual

ASSEMBLY, FIN, M131,M13lAl or MAU-103A/B

FUZE:.Refer to Bomb/Fuze Compatability

4C-34-1 — 1-(73)

Figure 1-72

M117 GENERAL PURPOSE (GP) BOMB

Note

The M117 bomb with the MAU-103A/B fin
has the same ballistic trajectory as the M117
bomb with the M131, M131A1 fin; therefore,
the ballistic tables presented in T.O. 1F-4C-
34-1-2 are applicable.

The M117 is a general purpose bomb (figure 1-72)
normally used for demolition operations. The bomb
has a cylindrical metal body with an ogival nose and
a tapered aft section to which a conical fin assembly
is attached.

The basic structural material of the bomb is steel.
The bomb body is filled with approximately 400
pounds of high explosive. A fundamental character¬
istic of the explosive used is its relative insensitivity
to ordinary shock and heat incident to loading, han¬
dling, and transporting. The bomb is designed for
use with both a nose fuze and tail fuze to insure re¬

liability of functioning and to cause the desired ef¬
fect, which may be blast, mining, or fragmentation.

The M131 or M131A1 conical fin assembly consists
of an elongated fin cone and four identical stream¬
lined blades assembled perpendicular to the fin cone.
The fin cone contains four access holes. Two ac¬
cess holes of a modified oval shape approximately
6.5 inches long, provide for installation of the bomb
tail fuze and attachment of an ATU-35/B or ATU-
35A/B drive assembly (figure 1-115) when an M905
bomb tail fuze is installed. The arming wires are
threaded through safety devices in the fuze to main¬
tain the fuze in a safe (unarmed) condition until after
release. The adapter-boosters serve to accommo¬
date the body of the fuzes, and to contain a booster
charge which insures detonation of the high explosive
charge.

Operation of the bomb commences at release when
the arming wires are withdrawn, permitting the
fuzes to arm. Upon impact with the target, one or
both fuzes operate, igniting the explosive train which
relays and amplifies the blast in order to detonate
the bursting charge in the bomb. If either fuze (nose
or tail) malfunctions, the other will usually cause
detonation of the bomb.

Change 5

1-169

T.O. 1F-4C-34-1-1

WEIGHT.

.... 880 Pounds

LENGTH.

. . . . 7 Ft., 1 Inch

DIAMETER.

.... 16 Inches

FINSPAN, CLOSED ....

.... 22.4 Inches

FINSPAN, OPEN.

. . . . 83.5 Inches

FLIGHT LIMITS.

.... Refer to Flight Manual

RETARDING TAIL ASSEMBLY

.... MAU-91 A/B
or MAU-91B/8

FUZE.

Refer to Bomb/Fuze Compatibility

40—34-1-1—( 74 )

Figure 1-73

M117R (RETARDED) GP BOMB

The M117R bomb (figure 1-73) consists of an M117
warhead with the MAU-91A/B or MAU-91B/B re¬
tarding tail assembly installed. The MAU-91 fin
assembly provides the cockpit selectable, high or
low drag delivery option. The fin assembly replaces
the standard M131 conical fin shown in figure 1-72,
and is configured for a high or low drag deployment
by methods of arming wire routing. The AC selects
the desired option through the arm nose/tail switch
on the pedestal panel. (Refer to Arming Wire/
Lanyard Routing, and figure 1-105.)

If the in-flight high/low drag release option
is used, the prescribed arming wire routing
must be utilized and the warnings and notes,
listed in Mission Description, parts 1, 2, or
3, must be carefully observed.

The fin assembly consists of four extentable drag
plates attached to the bomb body by a flange and

support tube. In the low drag configuration, the drag
plates are held closed by a release band. In high
drag configuration, the release band latch is pulled
by a lanyard attached to the arming solenoid in the
bomb rack, allowing the drag plates to deploy. The
drag plates are snapped open by a leaf spring under
each plate and by the airstream. The drag plates
stop approximately perpendicular to the airstream
to provide maximum drag area and stability.

Note

Ml 17 silhouettes and methods of arming wire
routing for the high/low drag options are
shown in section n, part 4.

M117D DESTRUCTOR

The M117 destructor is identical to the M117R ex¬
cept that the weapon is fuzed with components of the
MK 75 Mod 0 kit. The weapon is released high drag
only, and for ground implant and subsequent land
mine operations. Ballistic data is the same for both
M117R and M117D bombs. (Refer to section R part
4, Exterior Inspection for M117R bomb.)

Change 5

1-170

T.O, 1F-4C-34-1-1

BOMB DRAG INDEX.

. . . . 10.1

WEIGHT.

. . . . 3,020 Pounds

LENGTH.

. , . . 15 ft. 5 Inches

DIAMETER.

. . . . 24.13 Inches

FINSPAN.

. . . . 33.6 Inches

SUSPENSION LUG.

. . . . 30.0 Inches

FLT LIMITS.

. . . . Refer to FI ight Manual

FUZE:.

SUSPENSION EQUIPMENT

BRU-5/A Ejector Rack;

. . . . Refer to Bomb/Fuze Compatability

DRAG:.

. . . . 0

WEIGHT:.

. ... 45 Pounds

Figure 1-74

M118 GENERAL PURPOSE (GP) BOMB

The M118 GP bomb (figure 1-74) is normally used
for demolition operations (blast and mining). The
bomb is loaded with approximately 1888 pounds of
80-20 tritonal which constitutes approximately 62
percent of the total weight. The bomb is adapted for

use with nose or tail fuze. The Ml 18 GP bomb is
suspended from the BRU-5/A centerline bomb rack
on aircraft that have been modified with arming
solenoids at the centerline station (T.O. 1F-4-750).
The bomb is released through the nuclear release
system or through the conventional release system
if a shorting plug is used. Refer to sections II and III
for normal and emergency release procedures.

1-171

T.O. 1F-4C-34-1-1

MC-1 6AS BOMB

WEIGHT, EMPTY.

500 Pounds

WEIGHT, FULL.

720 Pounds

LENGTH.

7 Ft., 6 Inches

DIAMETER.

16.0 Inches

FIN SPAN.

22.38 Inches

SUSPENSION LUG DISTANCE . .

14.0 Inches

FLIGHT LIMITS.

Refer to Flight Manual

ASSEMBLY, FIN, MI31, M131A1 or MAU-103A/B

FUZE.Refer to Bomb/Fuze Compatability

4C-34-1-1-C76)

Figure 1-75

MC-l GAS BOMB

The MC-1 (figure 1-75) is a nonpersistent gas bomb
designed by conversion and modification of the Ml 17
general purpose bomb. The bomb has a cylindrical
metal body-with an ogival nose and a tapered aft sec¬
tion to which a conical fin assembly is attached. The
basic structural material of the bomb is steel. The
bomb body is filled with 24 gallons (220 pounds) of
GB agent. The filler tube is permanently welded
shut at the time filling is accomplished. The bomb
is designed for use with both a nose fuze and a tail
fuze. A hollow burster tube runs through the center
of the bomb and connects the nose and tail cavities.
Fuze wells are installed at both ends of the tube to
accommodate nose and tail fuzes. Prior to loading,
an M32 burster charge containing an explosive is in¬
stalled in the tube.

The M131 or M131A1 fin assembly consists of an
elongated fin cone and four identical streamlined
blades assembled perpendicular to the fin cone. The
fin cone contains four access holes. Of the autho¬

rized fuzes, any nose fuze (and components) may be
used with any tail fuze (and components).

Not*

Regardless of the fuze used, all will be set

for instantaneous or non-delay functioning.

Other components used are arming wires and
adapter-boosters. The arming wires are threaded
through safety devices in the fuze, thus maintaining
the fuze in a safe (unarmed) condition until release.
The adapter-boosters serve to accommodate the body
of the fuzes, and to contain a booster charge which
insures proper operation of the burster charge. Op¬
eration of the bomb commences when it is released
from the aircraft and the arming wires are with¬
drawn. This permits the fuze arming vanes to rotate
in the airstream. After the required number of rev¬
olutions or number of seconds, the fuzes are armed.
When the bomb impacts, the fuzes function, causing
the burster to detonate. The detonation of the
burster ruptures the bomb body and disperses the
filling as tiny droplets of liquid which quickly evapo¬
rate to a gas.

1-172

Change 5

mm n leaflet bomb

Ksac

" r • . • T’I* I*

•• 1

, <■*•

saw

■v

WEIGHT, EMPTY.92 Pounds

WEIGHT, FULL.200 Pounds (Depends

on weight of paper)

LENGTH.. 7 Ft., 6.02 Inches

DIAMETER.16.02 Inches

FIN SPAN. 22.78 Inches

SUSPENSION LUG DISTANCE .... 14.0 Inches

FLIGHT LIMIT.Refer to Flight Manual

ASSEMBLY, FIN M148

FUZES:.Refer to Bomb/Fuze Comparability

4C-34-l-l-(77)

M129E1, E2 LEAFLET BOMB

The M129E1, E2 (figure 1-76) is a leaflet bomb de¬
signed for use in delivery and distribution of leaflet
type materials. The bomb has a cylindrical body
with an ogival nose and a tapered aft section. It is
constructed of fiberglass and has an external con¬
figuration similiar to the M117 GP bomb. The bomb
body is split longitudinally into two sections which
are held together by four latches on each side. A
steel reinforcing plate below the suspension lugs is
added for forced ejection from the MER and TER.

The M148 conical fin assembly consists of four fiber¬
glass sections, glued and riveted together to form a
cone about 20 inches long. Four fin blades approxi¬
mately 23 inches long are attached to the cone. The
fuze well, which is located in the nose of the bomb
body, will accommodate a mechanical time fuze de¬
signed for airburst operation. No tail fuze is used
or provided for in the M129E1, E2 bomb.

Other components include an arming wire, an
adapter-booster assembly, and detonating cord
(Primacord). The arming wire is threaded through
the fuze safety device, thus maintaining the fuze in a
safe (unarmed) condition until release. The adapter-
booster accommodates the fuze and maintains the
detonating cord in the proper position. The detonat¬
ing cord is used to affect separation of the two bomb
body sections.

Operation of the bomb occurs a predetermined num¬
ber of seconds after release. Functioning of the fuze
causes the booster to ignite and detonate the 12-foot
length of Primacord. The Primacord is inserted
through the adapter-booster and longitudinally
around the entire bomb. Detonation of the Primacord
separates the two body sections, detaches the fins
and allows the leaflets to be released and scattered.

If the nose fuze fails to function, the bomb will dis¬
integrate upon impact.

Change 5 1-173

Figure 1-76

T.O. 1F-4C-34-1-1

MK 82 (SNAKEYE1) GP BOMB

MK 15 SERIES FIN

HIGH/LOW DRAG FIN:
WEIGHT.

LENGTH.

DIAMETER .

FINSPAN (CLOSED).

FINSPAN (OPEN).

FIN ASSEMBLIES .

.MK 15 Mod 3,3A, 4

FUZES:

MK 36.

MK 82.

M904E2, M904E3

'IC-34—1-1_(73—1>

Figure 1-77

MK82 (SNAKEYE I) GP BOMB

The MK 82 Snakeye I bomb (figure 1-77) is a general
purpose (GP) bomb with a MK 15 Mod 3,3A, or 4 tail
assembly. The nose of the bomb has a 3-inch wide
yellow strip that signifies high explosive filling. The
Snakeye I bombs provide the cockpit selectable, high
or low drag delivery option. The fin assembly is
configured for a high or low drag deployment by
methods of arming wire routing. The AC selects the
desired option through the arm nose/tail switch on
the pedestal panel. (Refer to Arming Wire/Lanyard
Routing, and figure 1-105.)

WARNING

If the in-flight high/low drag release option
is used, the prescribed arming wire routing
must be utilized and the warnings and notes,
listed in Mission Description parts 1, 2, or
3, must be carefully observed.

In the low-drag configuration, the folded retarder
blades form stabilizing fins. In the high-drag con¬
figuration, the four retarder blades are extended ap¬
proximately 90 to the longitudinal axis of the bomb.
The blades are hinged at the stationary clevis which
is screwed into the aft end of the retarder support.
Each retarder blade is linked to a sliding collar so
that all four retarder blades open at the same time.

The retarder blades are retained (folded) by a band
with a trunk-latch fastener, and the tail release wire
passes through the fastener.

Note

MK 82 silhouettes and methods of arming
wire routing for the high/low drag options
are shown in section n, pax-t 4.

HIGH DRAG RELEASE SPEED RESTRICTION

The maximum release speed of the MK 82 snakeye
when released high drag is dependent on which modi¬
fication of the MK 15 tail assembly is used:

a. The MK 15 Mod 0, Mod 1 and Mod 2 tail assem¬
blies are currently restricted from use on F-4 air¬
craft.

b. The MK 15 Mod 3, Mod 3A, and Mod 4 tail as¬
semblies are restricted to 500 KCAS maximum re¬
lease speed when released high drag.

MK36 DESTRUCTOR

This munition is the same as the MK 82 Snakeye I
bomb (figure 1-77) except that the fuze components
are those of the MK 36 destructor kit. The weapon

1-174

Change 9

T.O. 1F-4C-34-1-1

is deployed high drag only for ground implant and
subsequent land mine operations. Ballistic data is
the same for both the MK 82 Snakeye and MK 36
bombs. (Refer to section II part 4, Exterior Inspec¬
tion of MK 82 Snakeye bombs.)

M36 MOD 2/3 & MK 75 MOD 2/3
DESTRUCTOR KITS

These fuzing assemblies are available for use with
the high drag, and in addition the low drag versions
of the MK82 munition. For low drag/ground implant
operations however, certain release conditions must
be maintained in order to assure the proper function¬
ing of the munition and fuze system.

Note

MK82, MK83, MK84 LDGP BOMBS

The 80-series low-drag, general-purpose (LDGP)
bombs are illustrated in figures 1-78 thru 1-80. The
bombs are similar in shape, explosive used, and
construction; they vary in weight and size. The high-
explosive filler used in the bombs is Tritonal 80-20.
The external shape of the bombs is designed to pro¬
duce a minimum drag within the speed ranges of the
aircraft. The following list defines the quantity of
explosive contained in each bomb.

Bomb

Explosive Wt,

MK 82

192 Lbs.

MK 83

445 Lbs.

MK 84

945 Lbs.

For low drag/destructor employment, in¬
formation is available in T.O. 1F-4C-34-1-
1A. sections V and VI, regarding optimum
release parameters.

Change 9

1 -174A/(1 -174B blank)

F4-34-1-456

figure 1-79

BOMB DRAG NUMBER.1.8

WEIGHT. 985 Pounds

LENGTH.9 Ft., 10.5 Inches

DIAMETER.14 Inches

FIN SPAN.19.6 Inches

FUZE :.Refer to Bomb/Fuze Compatibility

FLIGHT LIMITATIONS :.Refer to Flight Manual

T.O. 1F-4C-34-1-1

MK82 LOW DRAG GP BOMB

BOMB DRAG INDEX . . .

.1.1

WEIGHT.

LENGTH.

DIAMETER.

FIN SPAN.

FUZE .

. Refer to Bomb/Fuze Compatability

FLIGHT LIMITATION: . .

. . Refer to Flight Manual

Figure 1-78

MK 83 LOW DRAG GP BOMB

00-5b

T.O. 1F-4C-34-1-1

BLU-1/B, B/B, C/B FIRE BOMBS
AND BLU-52/B, A/B CHEMICAL BOMBS

WT, EMPTY (Unfinned) .

. 82.5 Pounds

WT, FULL (Unfinned).

. 697 Pounds

WT. of FIN .

. 15 Pounds

WT of BLU-52/B, A/B.

. 350 Pounds

LENGTH without FIN.

. .. 11 Ft., 2 Inches

LENGTH with FIN .

. 12 Ft., 4 Inches

DIAMETER: .

. 19 Inches

SUSPENSION LUG DISTANCE: . . .

. 14 Inches

FLIGHT LIMITS: .

. Refer to Flight Manual

FIN: .

. . MXU-393/B or MXU-469/B

FUZE:.

. . Refer to Bomb/Fuze Compatibility

Figure 1-82

4C-34-1-1-(83)

BLU-l/B, B/B, C/B FIRE BOMBS

The fire bomb (figure 1-82) is an incendiary muni¬
tion. The basic structural material is aluminum with
a reinforced area below the lugs for sway bracing
and forced ejection. An initiator cavity is located
between the suspension lugs. The bomb is adapted
for use with both nose and tail fuzes and igniters. An
igniter cavity, for the igniter/fuze assembly, is lo¬

cated at each end of the bomb beneath the removable
nose and tail end caps (figure 1-116). Electrical
cables, internally installed in the bomb, electrically
connect the initiator and the igniter fuzes.

Operation of the bomb commences as it is force-
ejected from the MER or TER by extracting the arm¬
ing lanyard from the initiator, the arming lanyard is

Change 8

1-177

T.O. 1F-4C-34-1-1

WT, EMPTY (Unfinned) ....

• • • • 110 Pounds

WT, FULL (Unfinned)BLU-27/B

. . . . 832 Pounds

BLU-27A/B

. . . . 800 Pounds

WT. of FIN.

. ... 15 Pounds

LENGTH without FIN.

. . . . 11 Ft., 2 Inches

LENGTH with FIN.

, . . . 12 Ft., 4 Inches

DIAMETER:.

. . . . 19 Inches

SUSPENSION LUG DISTANCE .

.... 14 Inches

FLIGHT LIMITS: •.

. . . . Refer to Flight Manual

FIN:.

MXU-393/B or MXU-469/B.

FUZE:.

Refer to Bomb/Fuze Compatibility

Figure 1-83

retained by the arming solenoid. This permits a
firing pin to fire a thermal battery and electrically
arm the fuze. The fuzes function upon impact to
burst the igniter. The white phosphorus igniter
causes immediate ignition of the splattered fuel from
the required bomb. Typical fuze network for the fire
bomb is illustrated in figure 1-116.

Due to structural weakness of the end cap supports
attached to the nose and tail assembly, the end caps
can be expected to separate from the bomb during
falling and tumbling after it is released. This struc¬
tural weakness of the cap supports has been cor¬
rected in later production bombs.

BLU-l/B, B/B FIRE BOMBS

The BLU-l/B is identical to the BLU-1B/B except
the BLU-1B/B has an initiator adapter nut over the
initiator cavity and has higher suspension lugs.

BLU-1C/B FIRE BOMB

The BLU-1C/B fire bomb is identical to the BLU-
1B/B fire bomb except that the rear bulkhead has
been reversed so that option of using an end cap or a
fin assembly on the tail of the BLC-1C/B is available
after the bomb is filled. The BLU-1B/B does not
have this option after the bomb is filled.

BLU-27/B, A/B FIRE BOMBS

The BLU-27/B and A/B fire bomb (figure 1-83) is a
BLU-1B/B fire bomb that has been welded at the

4C_34-l-l-(84)

seams and loaded at the factory with Napalm B
incendigel mix. Napalm B is a slightly toxic, highly
viscous fluid. The BLU-27A/B has external arming
wire guides and is colored OD.

BLU-52/B, A/B CHEMICAL BOMBS

The BLU-52/B, A/B bombs (figure 1-82) consist of
the shell of the BLU-1C/B fire bomb, filled with a
white chemical powder. The BLU-52/B is prefilled
with CS-1 chemical agent and the BLU-52A/B is pre ¬
filled with CS-2 chemical agent. The bombs are
designed for external carriage on high performance
aircraft with forced ejection release systems but
can be released from low speed aircraft. When
employed with CS-1 or CS-2 filling, the bomb is
equipped with a tail fin and does not use a fuze or
initiator. The weight of the bomb varies with hu¬
midity and degree of packing.

FIRE/CHEMICAL BOMB FIN ASSEMBLIES

The MXU-393/B or MXU-469/B fin assembly is
designed for use with the BLU-l/B, B/B, C/B,
-27/B, A/B fire bombs; and the BLU-52 /b, A/b
chemical bombs. The assemblies, which stabilize
the bombs in flight, are made of aluminum and con¬
sist of four fin blades and a supporting structure.
The fin assemblies are interchangeable and produce
the same trajectory. Bomb length is increased ap¬
proximately 14 inches when a fin assembly is at¬
tached.

1-178

Change 5

T.O. 1F-4C-34-1-1

SUU-7 DISPENSERS

CBU-l, -2, SERIES WEAPONS

The CBU (Cluster Bomb Unit) weapon consists of the
SUU-7 (suspension and release unit) dispenser and
the BLU (Bomb, Live Unit) series bomblets. The
SUU-7 dispensers (figure 1-84) are cylindrical in
shape with a hemispherical nose and conical tail as¬
sembly. Nineteen thin aluminum tubes are shaped at
the tail end to fit the conical contour of the tail as¬
sembly.

CAUTION }

~ All SUU-7 series dispensers must be modi¬
fied with a ballast band to provide release
capability of the empty dispenser. The bal¬
last band is added to change the center of
gravity (CG) location of the empty dispenser.
This is necessary to prevent the ejection
force from causing the empty dispenser to
rotate upward and collide with the aircraft.

* Tube extensions are required on the CBU-l
and CBU-2 series dispensers at all stations
of the F-4C/D/E aircraft.

Note

* Only the CBU-2C/A (SUU-7C/A dispenser)
has an internal ballast band. The ballistics
data, description, and procedures appli¬
cable to CBU-2B/A is also applicable to
CBU-2C/A.

* When dispensing the CBU -46/A from the cen¬
ter line, the retainer cups may strike the
under side of the aircraft, causing super¬
ficial damage. This should not limit the op¬
erational use of this munition.

Ram-air through the opening in the nose dispenses
the BLU bomblets. The bomblets are retained in the
SUU-7 dispensers by means of an explosive detent
which fits into a keyway in the tube retaining plug.
This plug is the last item loaded in each tube. A
spring (unattached) and a piston (unattached) are
loaded at the forward end of each tube, ahead of the
bomblets. When the aircraft release circuitry fires
the explosive detent, this spring overcomes initial
tube-load inertia and starts the train of bomblets
moving rearward. Ram air pressure from the nose
of the dispenser acts on the piston to complete the
ejection sequence. Refer to figure 1-84 CBU com¬
ponents.

A panel on the forward upper section of the SUU-7
series may be removed to expose the tube selection
cannon plugs. Mating of these connections permits
tube sequencing to be selected. Early SUU-7 series
dispensers have 1-, 2- aiid 3- tube options, while
later dispensers are designed to permit 2-, 4-, and
6- tube options, and are identified as the SUU-7B/A
(CBU-2B/A) or SUU-7C/A (CBU-2C/A). Refer to
figure 1-84 for tube selection, identification and

firing sequence. This selection of tube option deter¬
mines the number of tubes which will be activated
with each release signal. The CBU harness should
never be connected except in an authorized arming
area. The ROCKET - CBU switch on the MER'sand |
TER's must be on CBU when CBU's are loaded.

The SUU-7A/A dispenser has anodized aluminum
tubes.

The CBU-1A/A is an anti-personnel weapon, con¬
sisting of the SUU-7 A/A dispenser loaded with BLU-
4/B bomblets. For further details on this munition,
see T.O. 11A1-5-6-51. The CBU series is a weapon
designed for use against personnel or light material
targets. The CBU-2/A consists of the SUU-7/A dis¬
penser loaded with 360 (17 tubes) BLU-3/B bomblets.
The CBU-2A/A consists of the SUU-7A/A dispenser
loaded with 406 BLU-3/B bomblets (19 tubes).

Note

Refer to the secret supplement (T.O. 1F-4C-

34-1-lB) for a description of the BLU-3/B

and associated information.

CBU-46/A DISPENSER AND BOMB

The CBU-46/A consists of 444 BLU-66/B antiper¬
sonnel bombs packaged in a SUU-7C/A bomb dispen¬
ser (figure 1-84). The SUU-7C/A dispenser is cy¬
lindrical with conical nose and tail sections, and has
19 thin walled aluminum tubes shaped at the tail end
to fit the conical contour of the tail assembly. The
dispenser has an internal ballast band required for
dispenser stability when jettisoned. (Only 18 of the
19 tubes in the CBU-46/A are loaded. The center
tube, tube K, is empty.) The conical nose cone has
an opening to allow ram air to dispense the bombs.
The bombs are retained in the dispenser by an explo¬
sive detent which fits into a keyway in the tube re¬
taining plug. This plug is the last item loaded into
each tube. A spring (unattached) and a piston (un¬
attached) are loaded at the forward end of each tube,
ahead of the bombs. When the aircraft release cir¬
cuitry fires the explosive detent, the spring over¬
comes initial tube load inertia and starts the train
of bombs moving. Ram-air pressure from the nose
of the dispenser acts on the piston to complete the
ejection sequence. Tubes may be ejected in a two-
tube, four-tube, six-tube, or salvo release. This
option is made by rotating the manual selector switch
with a screwdriver to the desired position before or
after the dispenser is attached to the aircraft. The
MER switch is positioned to CBU.

BLU-66/B Bomb

The BLU-66/B is an antipersonnel bomb, 2.8 inches
in diameter, 3.7 inches long, and weighs 1.5 pounds.
The bomb consists of a spherical fragmenting case,
a plastic impeller vane with a 2.2 inch diameter ob¬
turating disc, and a spin arm/spin decay fuze that
allows the bomb to penetrate a jungle canopy prior to
detonation. Upon release from the dispenser, the

Change 5

1-179

00-143

Figure 1-84 (Sheet 1 of 4)

Change 5

LENGTH . .
DIAMETER .
FLIGHT LIMIT
* CBU-1A/A:

CBU-2/A:

* CBU-2VA:

* CBU-2B/A:

* CBU-2C/A:

CBU-9/A:

CBU-9A/A:

CBU-9B/A:

CBU-12/A:

CBU-12A/A:

CBU-46/A:

.9 Ft., 10.4 Inches

.15.62 Inches

.Refer to T.O. 1F-4C-1

SUU-7^/A Dispenser with BLU-4A/B Bombs
19 tubes filled with 509 bombs.

Loaded wt: 782 lbs. Empty wt: 151 lbs.
SUU-7A/A Dispenser with BLU-3/B Bombs.

1 7 tubes filled with 360 bombs.

Loaded wt: 779 lbs. Empty wt: 151 lbs.
SUU-7A/A Dispenser with BLU-3/B Bombs.

19 tubes filled with 406 bombs.

Loaded wt: 858 lbs. Empty wt: 151 lbs.
SUU-7EL/A Dispenser with BLU-3/B Bombs.

19 tubes filled with 409 bombs.

Loaded wt: 870 lbs. Empty wt: 158 lbs.
SUU-7C/A Dispenser with BLU-3/B Bombs.

19 tubes filled with 409 bombs.

Loaded wt: 870 lbs. Empty wt: 158 lbs.
SUU-7A/A Dispenser with BDU-28/B Bombs.

19 tubes filled with 409 practice bombs.

Loaded wt: 688 lbs. Empty wt: 158 lbs.
SUU-7B/A Dispenser with BDU-28/B Bombs.

19 tubes filled with 409 practice bombs.

Loaded wt: 688 lbs. Empty wt: 158 lbs.
SUU-7C/A Dispenser with BDU-28/B Bombs.

19 tubes filled with 409 practice bombs.

Loaded wt: 688 lbs. Empty wt: 158 lbs.
SUU-7B/A Dispenser with BLU-17/B Bombs.

16 tubes filled with 213 smoke bombs (Tubes
A, B and C are empty) .

Loaded wt: 650 lbs. Empty wt: 158 lbs.
SUU-7C/A Dispenser with BLU-17/B Bombs. 16
tubes filled with 213 smoke bombs (Tubes A, B
and C are empty). Loaded wt: 687 lbs. Empty
wt: 158 lbs.

SUU-7Q/A Dispenser with BLU-66/B Bombs
18 tubes filled with 444 bombs(Tube K is empty)
Loaded wt: 890 lbs. Empty wt: 158 lbs.

The dispenser must be modified with a ballast band
to permit release of the empty dispenser. The
weight of the ballast band (30 lbs.) is included
in the above weights, (T.O. 11A-155-127) .

The SUU-7C/A has an internal
ballast band.

♦ Tube extensions are required on all stations.

4C-34-1 —1-(85 —1)

T.O. 1F-4C-34-1-1

FIRING OPTIONS

CBU-2/A AND CBU-2A/A FIRING OPTIONS

FIRING OPTIONS

CBU-2B/A AND CBU-2C/A

SYMBOL EXPLATIONS

SYMBOL EXPLATION

Note

BOTH THE CBU-2/A AND CBU-2A/A
HAVE A SALVO CAPABILITY

F4.34.I-462-2

Figure 1-84 (Sheet 2 of 4)

1-181

SELECTOR

PLUG

TUBE RELEASE SELECTOR PLUG

SELECTOR PLUG -
FASTENING SCREW (2)

T.O. 1F-4C-34-1-1

STEPPER SWITCH
CONNECTOR

WIRED FOR

TWO-TUBE RELEASE

SPRING

TUBE COMPONENTS OF CBU-2/A

ADAPTER

PLUG

OBTURATED

EJECTION

PISTON

BLU-3 B

EXPLOSIVE DETENT

RETAINING PLUG

EXPLOSIVE BOLT

F4-34-1-462-3

Figure 1-84 (Sheet 3 of 4)

CBU COMPONENTS

BLU-3/B

T.O. 1F-4C-34-1-1

BLU-17/B SMOKE BOMB
Used with CBU-12/A,

A/A Dispensers

4C—34—1 -1—(85-4)

Figure 1-84 (Sheet 4 of 4)

vane induces spin about the central axis oi the bomb.
At approximately 3500 rpm the fuze will arm. After
arming, the bomb will detonate when the spin has
been reduced below 2000 rpm. The arming sequence
of the fuze is as follows: At 2500 rpm, two spring
loaded centrifugal locks are disengaged from the
slide-detonator assembly, at approximately 3500
rpm, centrifugal force acting on three symmetrical
weights lifts the spring-loaded firing pin from a
recess in the top of the slider-detonator assembly.
This action frees the unbalanced slider-detonator
assembly which centrifugally moves the detonator
in line. The detonator is locked in line with a spring
detent. When the spin rate has decayed to approxi¬
mately 2000 rpm, the spring load on the firing pin
exceeds the centrifugal force of the weights, and the

firing pin is released causing the bomb to detonate.
The total weight of the Cyclotol explosive is 0.26
pound.

Planning Data

The sight depression angle values listed in the CBU-
46/A bombing tables (T.O. 1F-4C-34-1-2) were com¬
puted to provide initial BLU-66/B impacts commenc¬
ing 750 feet short of the aimpoint. Refer to T.O. 1F-
4C-34-1-1A, section I, part 4 for impact pattern
dimensional information. A deflection error chart
(sectionVI, this manual) is used to determine the
deflection error induced by the spin motion of the
bomb after release. This deflection error is always
to the left.

Chang* 5

1-183

T.O. 1F-4C-34-1-1

SUU-B/A, AIA, DISPENSERS

TUBE NUMBER
DESIGNATION

TUBE FIRING
ORDER

DISPENSER

WEIGHT

SUU-13 DISPENSER CHECK

BOMB

INTERVALOMETER
SAFETY PIN

157 Pounds

14.7 x 14. 4 Inches

8 Feet, 5.2 Inches

7 Feet, 8.8 Inches

7 Feet, 6.3 Inches

EMPTY WEIGHT.

WIDTH & HEIGHT.

LENGTH W/REAR FAIRING .
LENGTH W/O REAR FAIRING
LENGTH W/BOBTAIL FAIRING
NUMBER OF TUBES ....

INTERVALOMETER
SAFING SCREW

4 FORWARD

BOTTOM VIEW REAR fc

Figure 1-85

I CBU-12/A, A/A DISPENSERS AND
BOMBS

The CBU-12/A smoke producing weapon (1-84) con¬
sists of the SUU-7B/A dispenser and the BLU-17/B

I smoke bomb. The CBU-12A/A consists of the
SUU-7C/A dispenser and BLU-17/B smoke bombs.
The SUU-7B/A dispenser is cylindrical in shape

with a round nose and conical tail. (See CBU-2B/A
descriptive data.) The CBU-12/A, A/A carries
213 BLU-17/B smoke bombs which discharge white
phosphorus (WP) into the atmosphere when the
burster charge functions. The top three tubes (A,
B, and C) are not loaded. The BLU-17/B smoke
bomb will discharge white phosphorus (WP) over a
105-foot radius.

1-184

Change 5

LENGTH.7 Ft. 6 Inches

DIAMETER.16.0 Inches

SUSPENSION LUG DISTANCE.14.0 Inches

FLIGHT LIMITS.. Refer to Flight Manual

FUZE ..Refer to Bcmb/Fuze Compatability

-49, -52, -58, -70,

30C/B

24C/B

29C/B

49C/B

30H/B

52B/B

58/B

71/B

61A/B

63/B

86/B

30B/B

24B/B

26/B

665

29B/B

36/B

49B/B

59/B

52A/B

61A/B

217

70/B

85/B

4C — 34—1 — 1—(87)

CBU-24, -29,

BLU-26/B, -36/B, -59/B, -61A/B
-63/B BOMB

Figure 1-86

SUU-30 DISPENSERS

SUU-30/B DISPENSER

The SUU-30/B dispenser is divided in half longitudi¬
nally. The upper half contains the strongback section;
the lower half contains a reinforced hardshell area
for reinforcement while stored on chocks. The dis¬
penser skin is of low alloy, high strength steel. The
two halves are locked together by a nose locking cap
at the forward end and by a base plate screwed into
both halves at the aft end. Two MK 6 Mod 0 lugs
(14-inch suspension) are mounted on metal rods which
extend through the dispensers and attach to the bottom
half. A dual set of external arming wire guides is po¬
sitioned along the top half to prevent excess arming
wire vibration and to route the arming wire around
the MER/TER ejector foot. Two identical dual-fin
attachments are located on the aft end of the dispenser

body. The fins are canted 2-1/2° to impart spin to the
dispenser when released from the aircraft. The
wrought aluminum alloy fins are mounted in (x) con¬
figuration. The M907 mechanical time fuze is used.

SUU-30A/B DISPENSER

The SUU-30A/B dispenser is basically a SUU-30/B
dispenser which has been modified to eliminate the
tension members and to incorporate a fin assembly
modification to provide improved aerodynamics.
Specific changes are removal of the fin cant, in¬
creased chord length, and the addition of tip plates:
the fin span is not changed. Two MAU-76/A lugs
are used for suspension. The basic dispenser func¬
tion is not affected by these modifications. The M907
mechanical time fuze is used.

Change 7

1-185

T.O. 1F-4C-34-1-1

SUU-30B/B DISPENSER

The SUU-30B/B is constructed to accommodate the
M907 fuze, the FMU-56/B, A/B, B/Bfuze, and the
FMU-26A/B, B/Bfuze. Except for the nose sec¬
tion and the installation of a lanyard attachment stud
behind the aft suspension lug, the dispenser is iden¬
tical to the SUU-30A/B. The nose section of SUU-
30B/B contains a nose cap, coupling, adapter and
plug, breech cap and lanyard tube. The stud be¬
tween the aft suspension lug and the tail fin provides
an attachment point for lanyards used with FMU-
26A/B, B/BandFMU-56/B, A/B, B/Bfuze. Refer to
figure 1-106 for Arming Wire/Lanyard Configuration.

Note

The M907 fuze is physically compatible with
the SUU-30B/B dispenser, however the fuze
is unreliable with the SUU-30B/B and should
not be used.

SUU-30C/B DISPENSER

The SUU-30C/B dispenser is identical to the SUU-
30A/B except for the internal reinforcing rings to
support the hard backs. The M907 mechanical time
fuze is used.

SUU-30 H/B DISPENSER (CBU-58B)

The CBU-58/B consists of the SUU-30H/B dispenser
and approximately 650 BLU-63/B bombs. The SUU-
30H/B dispenser is identical to the SUU-30B/B dis¬
penser (figure 1-86) except that the fin tip plates are
1.50 inches shorter and are attached vertically on
the trailing edge of the fin. The BLU-63/B has ap¬
proximately the same size, weight, external ap¬
pearance, and uses the same fuze, booster pellet,
and explosive as the BLU-26/B. Functional charac¬
teristics of the CBU-58/BLU-63 are therefore simi¬
lar to those of the CBU-24/BLU-26.

M907 MECHANICAL TIME FUZE

The M907 nose fuze (figure 1-108) is an air-armed,
air-burst, mechanical time fuze with a black powder
booster. The M907 fuze is attached to the dispenser
nose locking ring. Fuze function times are from 4
to 92 seconds and are set prior to flight. The fuze
has an air-burst functioning accuracy of ± 1 second
over a temperature range of -65°F to +160 U F. Refer
to Bomb Fuzes for a detailed description of the
M907 fuze.

FMU-26A/B, -26B/B ELECTRIC TIME FUZE

The FMU-26A/B (figure 1-110) FMU-26B/B (figure
1-111) bomb fuze is an electronically timed fuze
that may be used on the CBU-24B/B, CBU-29B/B or
CBU-49B/B. The fuze is cylindrically shaped and
fits into the fuze well in the nose of the munition.
Delay settings on the fuze provide a selection of op¬
erating modes. External components of the fuze con¬
sist of a housing, cover plate, safing plug, safe-pin

assembly, seal pin, and booster. The safing plug is
replaced by a battery firing device when the fuze is
installed in a munition and prepared for use.

FMU-56/B, A/B, B/B PROXIMITY FUZES

The FMU-56/B (figure 1-114) is a self-powered
doppler radar proximity fuze used to open the CBU-
24B/B, -29B/B, -49B/B at a preselected altitude
AGL. The fuze has nine adjustable arming times
from 2 to 18 seconds and nine burst height settings.
Refer to T.O. 1F-4C-34-1-1A for burst height set¬
tings. Refer to FMU-56/B Proximity Fuze and FMU-
56A/B, B/B Proximity Fuze, this part, for more
detailed information.

CBU-24/B, A/B, B/B, C/B DISPENSERS AND BOMBS

The CBU-24 series contains the BLU-26/B bomb,
designed for use against personnel and light material
targets. See figure 1-86 for SUU-30 designation.

BLU-26/B Bomb

The BLU-26/B is contained in the CBU-24 series
dispensers. The BLU-26/B bomb (figure 1-86) is a
spin armed, self-dispersing, fragmentation submu¬
nition that detonates upon impact. When the bomb is
released into the air stream, the bomb begins to spin
at a high rate. This spinning action is caused by the
bomb flutes. Spinning enhances bomb dispersion and
initiates arming the M219 fuze. The weights that hold
the rotor in the unarmed position are released by
the centrifugal force of the spinning bomb. As the
hammer weights move back, the firing pin is re¬
leased from the rotor. Disengagement of the weights
which hold the rotor in the unarmed position allows
the rotor to arm. The M219 fuze is sensitive to im¬
pact from any direction. Impact with a target det¬
onates the high-explosive filler which bursts the
bomb case and propels the steel balls at high veloc¬
ity in a radial direction.

Note

Since certain fuzing and arming criteria must
be met, it is necessary to carefully preplan
and execute any mission involving the delivery
of the CBU-24/B, A/B, B/B, C/B. To assure
adequate time for the bomblet (submunition)
to spin-up and arm, do not select burst heights'
lower than those presented in the bombing
tables (T.O. 1F-4C-34-1-2)for various re¬
conditions.

CBU-29/B, A/B, B/B, C/B DISPENSERS AND BOMBS

The CBU-29 series contains the BLU-36/B bomb,
designed for use against personnel and light material
targets. See figure 1-86 for SUU-30 dispenser desig¬
nation. See T.O. 1F-4C-34-1-1A for the delay time
of the random detonating fuze of the BLU-36/B bomb.

1-186

Change 6

T.O. 1F-4C-34-1-1

BLU-36/B Bomb

With the exception of bomb fuzing, the CBU-29 and
CBU-24 series munitions are identical. The BLU-
36/B bomb used with the CBU-29/B, A/B, B/B,

C/B is equipped with an M218 time delay fuze which
detonates randomly after impact. Refer to T.O. 1F-
4C-34-1-1A for M218 delay time.

CBU-49/B, A/B, B/B, C/B DISPENSER A BOMB

The CBU-49 series contains the BLU-59/B bomb.
See figure 1-86 for SUU-30 dispenser designation.

BLU-59/B Bomb

The BLU-59/B is contained in the CBU-49 series
dispensers. With the exception of bomb fuzing, the
BLU-59/B and the BLU-26/B are identical. The
BLU-59/B bomb is equipped with an M224 time de¬
lay fuze which detonates randomly after impact. The
time period for all M224 fuzes to detonate is sub¬
stantially less than the BLU-36/B.

CBU-52A/B DISPENSER & BOMB

The CBU-52A/B consists of the SUU-30B/B dis¬
penser (figure 1-86) and 217 BLU-61A/B bombs.

The functional sequence is identical to the CBU-
24B/B system.

CBU-52B/B DISPENSER AND BOMB

The CBU-52B/B consists of the SUU-30H/B dis¬
penser and 217 BLU-61A/B bombs. The functional
sequence of the CBU-52B/B is identical of that
sequence for the CBU-24B/B and CBU-52A/B muni¬
tion systems.

BLU-61A/B Bomb

The BLU-61A/B is a 3.3 inch diameter, self-dis¬
persing, spherical, high explosive/fragmentation
bomb which is designed for use against materiel
targets. The bomb contains a zirconium liner to
provide an incendiary capability and employs the
M219 fuze. Ballistic tables and impact pattern data
are provided in T.O. 1F-4C-34-1-2.

CBU-71/B DISPENSER AND BOMB

The CBU-71/B dispenser and bomb consists of the
SUU-30H/B dispenser loaded with approximately
650 BLU-86/B fragmentation bombs.

BLU-86/B Bomb

With the exception of bomb fuzing, the BLU-86/B
and BLU-63/B bombs are identical. The BLU-86/B
bomb is equipped with a M224 time delay fuze which
detonates at random times after impact.

CBU-70/B DISPENSER AND BOMB

The CBU-70/B consists of the SUU-30 B/B dispenser
and 79 BLU-85/B multiple linear shaped charge

(MLSC) submunitions. The FMU-26 or FMU-56
series fuzes may be used to function the dispenser
at the preset time after release or altitude above
ground.

BLU-85/B Bomb

The BLU-85/B weighs approximately 5.8 pounds and
is 2.5 inches in diameter. The major components of
the BLU-85/B include a BLU-49/B fuze, and MLSC
warhead, a stabilizing ribbon and a stabilizing rib¬
bon housing with composition B explosive filler in
the warhead.

SUU-13 DISPENSERS

Refer to Rehoming MERS and TERS, part
1, 2, or 3.

SUU-13/A DISPENSER

The bomb packages are ejected from the SUU-13/A
dispenser when the bomb button is depressed. De¬
pressing the bomb button supplies power to fire an
electrically primed cartridge of one cylinder and
activates a stepping mechanism and a control inter-
valometer which continues to stepfire one tube at a
time until the bomb button is released. The pulse
rate (time spacing between tube firings) is con¬
trolled by a timing circuit. The rate of stepping is
preset on the ground by a selector switch in the dis¬
penser control box. The available pulse rates are
100, 200, 300, 400, and 500 milliseconds.

Only the RKTS & DISP/SINGLE mode can be used to
release the bomb packages from the SUU-13/A dis¬
penser. The release signal must be continuously ap¬
plied to the SUU-13/A timing circuit for a time dura¬
tion (4 to 19 seconds) determined by the dispenser
pulse rate setting: multiply the pulse rate setting by
39. However, the amber station select light will
normally go out when all dispensers on that station
have timed out. The bomb release button must be
released to cause the stepper switch in the MER/
TER to transfer to the next dispenser. When the
bomb button is released, stepping will occur even
if the previous dispenser is partially expended. The
MER and TER switch must be set on CBU.

The dispenser payloads are contained in the SUU-
13/A in a sealed cylinder assembly which also con¬
tains the explusion cartridge. The expulsion car¬
tridge is located within a high-pressure chamber.

The gas produced when the cartridge is fired is di¬
rected through a small orifice from this high-pres¬
sure chamber to a low-pressure chamber. The re¬
duced pressure limits the reaction on the dispenser.

SUU-I3A/A DISPENSER

The primary difference between the SUU-13/A and
SUU-13 A/A is the available pulse rates. The SUU-
13A/A available pulse rates are: 50, 100, 200, 300,
and 400.

Change 7

1-186A

T.O. 1F-4C-34-1-1

CBU-7A/A DISPENSER & BOMB

The CBU-7A/A weapon consists of the SUU-13A/A
downward ejection dispenser and BLU-18/B anti¬
personnel bomb packages and bombs. Refer to fig¬
ure 1-85.

The SUU-13A/A dispenser is constructed of high-
strength aluminum. The dispenser has a flat open
bottom, flat sides, a curved hardback section and
14-inch suspension lugs. The loaded SUU-13A/A
dispenser contains 40 tubes with 30 BLU-18/B bombs
contained in each bomb package per loaded tube for
a total of 1200 BLU-18/B bombs per dispenser.

The dispenser payloads (BLU-18/B packages) are
contained in the SUU-13A/A in a sealed cylinder as¬
sembly which also contains the expulsion cartridge.
The expulsion cartridge is a high-pressure chamber
The gas produced when the cartridge is fired is di¬
rected through a small orifice from this high-pres¬
sure chamber to a low-pressure chamber. The re¬
duced pressure limits the reaction on the dispenser
and produces a payload ejection velocity of approxi¬
mately 65 fps. Refer to the classified supplement to
this manual for additional information on this muni¬
tion.

1-186B

Change 7

T.O. 1F-4C-34-1-1

Pattern Length

The CBU-7A/A Ripple Release tables list the total
impact pattern length for a 40-bomb (i.e. 40-tube or
package ripple) ripple release at the various SUU-
13A/A intervalometer settings. The impact pattern
length is based on the distance between the mean
point of impact for the first and last cluster release,
The tabulated sight depression from flight path
values assume that the center of the pattern is to be
aimed at the target.

CBU-30/A DISPENSER AND BOMB

The CBU-30/A weapon consists of the SUU-13/A
downward ejection (dispenser and BLU-39/B23 anti¬
personnel bomb packages and bombs. Refer to fig¬
ure 1-85.

BLU-39/B23 Bomb Package

A BLU-39/B23 Bomb Package is carried in each of
the 40 tubes of the SUU-13/A dispenser. The BLU-

39/B23 package contains 32 BLU-39/B23 bomblets.
The package is ejected from the tube at approximate¬
ly 90 fps downward. The package has a fiberglass
case with aluminum end plates. A delay element al¬
lows the package to burst approximately 0.310 sec¬
ond after it is ejected from the dispenser to release
the bomblets. The package is unstabilized in flight.

The BLU-39/B23 package is cylindrically shaped
with the following physical characteristics:

Diameter 4.6 in.

Length 10.5 in.

Weight 9.7 lb.

BLU-39/B23 Bomblet

The BLU-39/B23 bomblet has a cylindrical shape and
looks very much like a flashlight battery. It has an
aluminum case, which contains 40 grams of material
(60% pyrotechnic and 40% CS). The bomblet has a
delay element so that it will not start to dispense its

Change 5

1-187

T.O. 1F-4C-34-1-1

CS (smoke) until 5 to 6 seconds after it is released
from the cluster. The bomblet dispenses CS for ap¬
proximately 10 to 15 seconds. When the bomblet im¬
pacts on a cleared surface it will skitter about, due to
the violent expulsion of the CS smoke from an orifice
in one end of the bomblet. The bomblet is unstabi¬
lized.

The BLU-39/B23 bomblet has the following physical
characteristics:

Diameter 1.25 in.

Length 2.5 in.

Weight 0.13 lb.

Not*

Since the bomblet will start to dispense smoke
5 to 6 seconds after release, release condi¬
tions which provide a time of flight of less
than 6 seconds should be selected.

Pattern Length

With a munition of this type, the impact patterns for
a single package are variable. For planning purposes,
the size of the impact pattern for a single package is
approximately 225 feet in range and 200 feet in de¬
flection. The CBU-30/A Ripple Release tables list
the total impact pattern length for a 40-package
(bombs per release) release at the various available
SUU-13/A intervalometer settings. This impact pat¬
tern length is based on the distance between the mean
point of impact for the first and last cluster release.
The tabulated sight depression from flight path values
assume that the center of the pattern is to be aimed
at the target.

CBU-38/A, A/A, (SUU-13A/A) DISPENSERS AND
BOMBS

The CBU-38/A consist of 40 BLU-49/B bombs re¬
spectively, installed in the SUU-13A/A dispenser.

The bombs are 4.6 inches in diameter, 10.25 inches
long when installed in the SUU-13A/A cylinder, 14
inches long with ringtail extended, and have a nom¬
inal weight of 13 pounds. The bombs are ejected
downward at approximately 62 fps from the SUU-
13A/A when an electric pulse ignites the propellant
charge of the ejection cartridge within the cylinders.
The resulting pressure buildup is sufficient to shear
six pins, which hold the bombs in the cylinder.

Three wind tabs within the bomb tail assembly force
the stabilizer ringtail into the extended position as
the bomb exits. Extension of the tail assembly
actuates the fuze system. The bomb arms in 5.5
sec ± 1.0 sec.

Note

For CBU-38/A, release conditions must be
selected which provide a BLU-49/B bomb
time of flight greater than 6.5 sec for all
bombs to assure adequate time for the fuzes
to arm prior to impact.

The CBU-38A/A consists of 40 BLU-49A/B bombs
installed in the SUU-13A/A dispenser. The BLU-
49A/B is identical to the BLU-49/B except for the
fuzing. The arming time for the BLU-49A/B was
reduced to a minimum of 2.25 seconds and a maxi¬
mum of 3.50 seconds. The BLU-49A/B has a safety
device that prevents the bombs from arming when
it senses an impact greater than 25 G after the
ringtail has been extended and before the arming
time (2.25 to 3.50 sec) is reached. The weight lock
was redesigned to prevent it from being misas-
sembled.

Note

For the CBU-38A/A, release conditions
must be selected which provide a BLU-
49A/B bomb time of flight greater than
3.5 sec for all bombs to assure adequate
time for the fuzes to arm prior to impact.

If the bomb must penetrate jungle canopy, the resul¬
tant deceleration should not be sufficient to cause the
inertial weights to fire the detonator. The bomb then
will penetrate and explode following final impact with
the ground. Upon water or mud impact (which does
not provide sufficient deceleration to fire the detona¬
tor by the action of the inertial weights), another
means is provided to fire the detonator. Openings in
the face of the fuze will allow the fluid media to en¬
ter and push a piston against the firing pin. The fir¬
ing pin then fires the detonator and ignites the ex¬
plosive train.

The CBU-38A/A bombing tables are also applicable
for the CBU-38/A. However, when releasing the
CBU-38/A, release conditions must be selected
which will provide a time of flight greater than 6.5
sec. For the dive release conditions, the time of
fall of the last bomb must be checked. These values
are contained in the bombing tables.

The CBU-38 bombing tables provide data for full
dispenser ripple releases at release intervals of
0.05, 0.10, and 0.20 sec.' The bomb range listed in
the tables represents the horizontal range from initial
release to the center of the impact pattern. The im¬
pact pattern length listed in the ripple release tables
for a 40-bay release represents the distance between
the impact points of the first and last bombs released.
A fixed dive angle aircraft flight path, throughout the
entire ripple release time cycle, was assumed in
this computation.

If the CBU-38 is carried on the shoulder positions
of either MER or TER, the BLU-49 impact pattern
will be displaced laterally in the direction of the
side ejection. The magnitude of this lateral dis¬
placement, which is induced by an effective lateral
munition ejection velocity component of approxi¬
mately 44 fps (62 x sin 45°), is indicated in the MER/
TER Shoulder Position Carriage tables. The quan¬
tities listed are measured from the point of ejection
and cover the range of release conditions provided
in the CBU-38 bombing tables.

1-188

Change 5

T.O. 1F-4C-34-1-1

SUU-36/A, -38/A DISPENSERS

11 Feet, 10 Inches
17 Inches
(SEE TEXT)

LENGTH, With Tail Fairings removed

HEIGHT.

REL. INTERVALS.

WEIGHT

NUMBER OF
CANNISTERS

EMPTY

CBU -

SUU-

BLU-

KMU-

33/A

36/A

45/B

339/B

34/A

38/A

42/B

338/B

34A/A

38/A

42A/fe

338/B

42/A

38/A

54/B

338/B

T.O. 1F-4C-34-1-1

SUU-36 DISPENSERS

CBU-33/A DISPENSER AND MINE

The CBU-33/A dispenser and mine consists of the
SUU-36/A dispenser (figure 1-87) and the BLU-45/B
antivehicle land mine. The CBU-33/A provides the
capability of emplacing a subterranean antivehicle
mine field from high performance fighter aircraft.
The SUU-36/A dispenser has 10 cargo bays, each
of which will accommodate three BLU-45/B mines.
At release, the dispenser control wiring harness,
which is installed in the strongback area of the dis¬
penser, transmits the 28 vdc pulses to initiate the
ejector cartridge in each cargo bay. The ejector
piston then accelerates the cargo (three stacked
BLU-45/B mines) to an ejection velocity of approxi¬
mately 20 feet per second. The interval between
ejector cartridge initiations is controlled by an in-
tervalometer in the right rear frustrum of the dis¬
penser. The available release interval settings are
38, 61, 92, 140, 200, and 300 milliseconds or
SINGLE. The desired release interval must be pre¬
set before flight.

Not*

The smallest available release interval, 38

milliseconds, is not cleared for use with the

BLU-45/B mine cargo.

Only the RKTS & DISP/SINGLE mode can be used to
release the canisters from the SUU-36/A dispenser.
To empty the dispenser, the release signal must be
continuously applied to the SUU-36/A timing circuit
for a time duration determined by the dispenser in-
tervalometer setting: multiply the intervalometer
setting by 29. The dispenser does not have a CBU
monitor circuit to establish an empty or full dis¬
penser. Releasing the bomb release button causes
the stepper switch in the MER/TER to transfer to
the next dispenser. The MER and TER switch must
be set on CBU.

Refer to T.O. 1F-4C-34-1-1A for additional infor¬
mation concerning BLU-45 kill mechanisms, self
destruct features, and minefield impact pattern data.

The CBU-33/A bombing tables provide basic data
for SINGLE releases and full dispenser ripple re¬
leases at each permissible release interval. The
tables for SINGLE release provides trajectory and
sight depression for a single cargo bay ejection of
three BLU-45/B mines. The bomb range listed in
these tables represents the horizontal distance from
ejection to the mean point of impact of the three
BLU-45/B mines. The BLU-45/B trajectory impact
angle, measured from the horizontal, is also listed.

The impact pattern length listed in the ripple release
tables for a 10-cargo bay release represents the
distance between the mean points of impact for the
first and last munitions released. The sight depres¬
sion from flight path and wind correction factor
values assume that the center of the impact pattern
is aimed at the target. The tabulated release slant
range value represents the distance between initial
release and the center of the impact pattern.

If the CBU-33/A is carried on the shoulder positions
of either MER or TER, the BLU-45/A impact pattern
will be displaced laterally in the direction of the side
ejection. The magnitude of this lateral displacement,
which is induced by an effective lateral munition
ejection velocity component of approximately 14 ft/
sec (20 x sin 45°), is indicated in figure 6-23. The
quantities listed are measured from the point of ejec¬
tion and cover the range of release conditions pro¬
vided in the CBU-33/A bombing tables contained in
T.O. 1F-4C-34-1-2.

SUU-38 DISPENSERS

CBU-34/A, A/A, -42/A DISPENSERS AND MINES

The CBU-34/A, A/A -42/A dispenser and mine
munitions consist of the SUU-38/A Dispenser (figure
1-87), a payload of mines, and a kit (KMU-338/B)
to cluster, retain, explosively eject, and initiate
dispersal of the mine payload. The basic SUU-38/A
dispenser has 10 cargo bays. Each bay is divided
into three separate compartments by an adapter to
provide a total of thirty KMU-338/B canister cargo
compartments. The KMU-338/B canister cargo is
held vertically in the SUU-38/A cargo bay. Each
KMU-338/B canister contains a cargo of 18 mines.
The mines are sub-munitions (BLU-42/B, A/B and
BLU-54/B series mines), spherical in shape with
four flutes which facilitate dispersal and arming
after the mines are released from the canister. The
KMU-338/B canister ejection velocity from theSUU-
38/B is approximately 30 ft/sec. The canister opens
to release the sub-munition mines approximately 0.7
sec after ejection. The KMU-338/B mine canisters
can be ejected at one of the following rates: 0.07,
0.20, 0.35, 0.50, 1.00, or 1.50 sec. The required
ejection rate must be set into the SUU-38/A dis¬
penser intervalometer prior to take-off. Only the
RKTS & DISP/SINGLE mode can be used to release
the canisters from the SUU-38/A dispenser. To
empty the dispenser, the release signal must be
continuously applied to the SUU-38/A timing circuit
for a time duration (2 sec. to 43.5 sec.) determined
by the dispenser intervalometer setting: multiply
the intervalometer setting by 29. The dispenser does
not have a CBU monitor circuit to establish an
empty or full dispenser. Releasing the bomb re¬
lease button causes the stepper switch in the MER/
TER to transfer to the next dispenser. The MER and
TER switch must be set on CBU. Refer to T.O. 1F-
4C-34-1-1A, section I, part 4 for classified de¬
scription and procedures to determine pattern length.
Refer to T.O. 1F-4C-34-1-2 for the ballistic tables.

Not*

Ballistic and impact pattern data is identical
for the CBU-34/A, and CBU-42/A dispensers
and mine munition.

M36E2 INCENDIARY CLUSTER BOMB

The M36E2 (figure 1-87A) is an incendiary cluster
munition designed to be used against wooden struc¬
tures, oil storage areas, and other flammable tar-

1-190

Change 5

OD-285

T.O. 1F-4C-34-1-1

M36E2 INCENdlARy CLUSTER BOMB

EXTERNAL STORE LIMITATIONS (Flight Manual)

WEIGHT. 900 Lbs

LENGTH.90 Inches

DIAMETER.16 Inches

FIN SPAN.23 Inches

CAPACITY Ml26 THERMITE (TH3) BOMBS . . . 177 Each
TAIL FUZES, MECHANICAL TIME M152A1 . . . . 2 Each

4C-34-1 —1-(89)

Figure 1-87A

gets. The dispenser assembly consists of two half¬
cylinder casings with a continuous piano-type hinge
locking system along the sides of the case halves.
The upper case contains the 14-inch supsension lugs
and an internal hard-back to sustain forced ejection.
Separation of the casings is accomplished by the de¬
tonation of a 22-foot length of detonating cord which
is threaded through the hinge locking device assem¬
bly. A nose cone (or plate) is not used for F-4 car¬
riage. A fin cone is bolted in X configuration to the
cylinder body. Two fuzes are installed in fuze wells
(180° apart) in the fin cone. The fuzes are mechani¬
cal time type, and allow the cluster to be opened at
a predetermined time after drop from the aircraft.
Detonation of either fuze will open the dispenser.

INCENDIARY

The dispenser contains 176 M126 thermite bombs
(4-lbs each). The bomb is hexagonal with a blunt
cast iron nose and with 3 retractable fins that extend
at bomb/dispenser separation. The body is con¬
structed of magnesium alloy and is 1.6 inches across
the hexagon and 19.5 inches in length. An inertia-
type fuze is located between the bomb body and fin.

DISPENSER FUZES

The tail cone fuze wells receive the Ml 52A1 tail
fuze (2) mounted in-line with the dispenser hinges.
The M152A1 is manually set to function from 5 to 92
seconds after arming wire separation.

Change 7

1-190A

T.O. 1F-4C-34-1-1

MK 20 MOD 2 AND MOD 3 CLUSTER
BOMB (ROCKEYE II)

The MK 20 Mod 2 or Mod 3 Cluster Bomb (figure
1-88) consists of the MK 7 Mod 2 or Mod 3 folding
dispenser containing 247 MK 118 Mod 0 anti-tank
bombs (figure 1-88). The clusters are prefuzed with
an MK 339 Mod 0 mechanical time fuze.

The MK 7 Mod 2 bomb cluster consists of a nose
fairing, a cargo and tail section. The nose fairing
houses the MK 339 Mod 0 mechanical time fuze.
During ground handling and loading, a fuze cover is
installed over the fuze impeller and the fuze safety
wire. The aluminum skinned cargo section houses
the MK 118 Mod 0 anti-tank bombs which are se¬
cured and protected by dunnage. A linear-shaped
charge is secured to the inner wall of the cargo sec¬
tion. This shaped charge is used to cut the cluster
in half longitudinally when the fuze functions after
release which allows the MK 118 Mod 0 bombs to
spread in freefall trajectory. The bombs arm shortly
after release from the dispenser and detonate upon
impact. The tail section consists of a conical body

equipped with four foldable, spring-loaded fins.

Until release, these fins are held in the folded po¬
sition by a fin release wire and for ground safety,
a fin safety pin. Two conduits are provided along
the top of the bomb cluster for routing the fuze arm¬
ing wire and the fin release wire. All components,
including fuze and fuze arming wires are installed
in or on the bomb cluster during manufacture to
make a complete munition. Two suspension lugs,
spaced 14 inches apart, are installed in the bomb
cluster.

The MK 7 Mod 3 bomb cluster is identical to the
MK 7 Mod 2 bomb cluster with one exception. On
the MK 7 Mod 3, a pilot option wire has been added
to the MK 339 Mod 0 fuze to allow the pilot to select,
in the air, one of the two fuze function times set on
the fuze. The conduit for the fuze wire was modified
to allow for routing of the pilot option wire.

MK 339 Mod 0 Mechanical Time Fuze

The MK 339 Mod 0 fuze (figure 1-88) is a nose-
mounted, mechanical time fuze designed for use

1-190B

Change 7

T.O. 1F-4C-34-1-1

with bomb type dispenser munitions. The fuze has
two selectable functioning times, primary and option,
with a setting range of 1.2 to 50 seconds in 0.1 sec¬
ond increments for each functioning time. Any set¬
ting within the above range may be selected for
either functioning time. In the MOD 3 bomb, an
option wire is added to allow the AC to select (in
flight) one of two fuze function times. This is the
essential difference between the Mod 2 and Mod 3
munitions. The Mod 2 fuze functioning time is pre¬
set at the time of manufacture to 4.0 seconds but
may be reset before flight. The Mod 3 fuze func¬
tioning times are preset to 1.2 seconds (primary)
and 4.0 seconds (option) and armament crews may
reset these times before flight. The functioning
time used is determined by the position of the fuze
option pin. The option pin is normally held depressed
by an option wire which is installed at the time of
manufacture. With the option wire installed and the
option pin depressed, the fuze will function at the
expiration of the selected primary time. When the
option wire is pulled allowing the option pin to ex¬
tend, the fuze will function at the expiration of the
selected option time. Once the option wire has been
removed, it cannot be reinstalled and the fuze is
committed to the option time setting.

At the time of installation into the MK 20 Mod 2
bomb cluster, the MK 339 fuze option wire is re¬
moved, disabling the fuze primary time capability.
However, the fuze option time capability and set¬
tings are not affected. When installed in the MK 20
Mod 3 bomb cluster, the bomb cluster is configured
with an option wire for the fuze allowing utilization
of either the primary or option time setting as the
mission requires. The aircrew selects the time to be
used by pulling or not pulling the option wire at
weapon release. The option wire is secured in the
ejector rack rear solenoid. The option timer func¬
tions with an accuracy of ± 0.1 second for settings
from 1.2 to 10 seconds, and 1.0% of all settings over
10 seconds.

The arming wire secures both the impeller and the
timer starting pin until the wire is withdrawn at re¬
lease. The arming wire is secured in the forward
rack solenoid.

For the Mod 3 munition, the arm nose tail switch is
positioned to get either of the two (primary or op¬
tion) functions in the following manner.

Mod 3 Function Arm N/T Switch

Primary Nose

Option Nose & Tail

A fuze SAFE/ARM indicator under a clear plastic
bubble is viewed through the observation window in
the upper nose fairing of the dispenser. The fuze is
armed when the end of the indicator pin (red) is
visible at the base of the plastic indicator bubble.

MK 118 MOD 0 BOMB

I The MK 118 Mod 0 anti-tank bomb (figure 1-88) con¬
sists of the MK 1 Mod 0 bomb fuzing system, a

shaped charge warhead, and fixed, stabilizing fins.
When the cluster splits at fuze functioning, the MK 1
Mod 0 bomb fuzing system arms the bomb and the
same system detonates the bomb on impact. The
shaped charge warhead causes the explosive force
of the detonation to be directed forward into the im¬
pact point. Refer to T.O. 1F-4C-34-1-1A for addi¬
tional information.

MK 20 MOD 2, 3 Bombing Tables

The bombing tables provide mission planning data
for the WRCS dive toss bombing, low altitude level
and 10° dive releases using 1.2 to 8.0 sec fuze func¬
tion times, and higher altitude level and dive re¬
leases where the dispenser is to be opened at a pre¬
planned altitude above ground.

WARNING

To protect the aircraft and aircrew if the
cluster does not open as planned and the in¬
tact munition detonates high-order at initial
impact, the following minimum release alti¬
tudes and associated escape maneuvers should
be observed during low altitude level or 10°
dive releases where the 1.2 fuze function set¬
ting is used.

Release Altitude

800 ft AGL
400 ft AGL

900 ft AGL

SUU-25A/A

Release Angle Escape Maneuver

0° Straight and Level

0° 4 G wings-level

pullup or 4 G60°
banked turn

10° 4 G wings-level

pull up

FLARE DISPENSER

The SUU-25A/A flare dispenser (figure 1-89, sheet
1) contains four tubes, each capable of receiving
two MK 24/LUU-2/B flares or LUU-l/B, 5/B, 6/B
target markers. A compressed spring in each tube
applies the rearward ejection force when the flares
or markers are deployed. After a pair of flares or
markers are inserted into the tube against the spring,
end plugs are installed, and then explosive detents
are installed to retain these units against the spring
tension. When the AC deploys a pair of flares or
markers, the release pulse detonates the explosive
detents and the spring ejects the flares or markers
rearward.

For ground safety purposes, a shorting device is in¬
stalled into the aft dispenser electrical receptacle to
interrupt the detent circuits. Prior to takeoff, the
shorting device is removed and the MER electrical
connector is installed. The safety pins with red flag
attachments are installed over the end plugs to me¬
chanically safe the ejection system (figure 1-91). To
eject the flares or markers, cockpit switching pro¬
cedures are the same as those for CBU dispensers.

Each flare contains controls (figure 1-89, sheet 2) to
set parachute ejection delay time (from 5 to 30 seconds),
and flare ignition delay time from 10 to 30 seconds

Change 7

1-191

T.O. 1F-4C-34-1-1

FUZE

COVER

FIN RELEASE BAND

MK 7 Mod 2 & Mod 3
. 476 Pounds
, 7 Foe*, 8 Inches
, 13.2 Inches
. 34.5 Inches
. MK 339 Mod 0

DISPENSER .

WEIGHT .

LENGTH (With Fuze)
DIA. (Fins Retracted)
(Fins Extended)
FUZE .

- SAFE/ARM
OBSERVATION
WINDOW

MK 118 Mod 0
247 Bombs
2.1 Inches
1 3.5 Inches
1.32 Pounds

BOMB . (An
CAPACITY
DIAMETER
LENGTH .
WEIGHT ..

FUZE SAFE/ARM
INDICATOR

OPTION WIRE
(MOD 3 ONLY)

-TIMER

SET

WINDOW

OPTION
PIN —

— TIMER
OBSERVATION
WINDOW
(MOD 3 ONLY)

IMPELLER
SEALING
BAND —

- TIMER
STARTING
PIN

IMPELLER

- OPTION
TIME SETTER

PRIMARY

TIME

SET

SAFETY WIRE
AND WARNING TAG
(REMOVE BEFORE FLIGHT)

ARMING

WIRE

- BAND
RELEASE
STUD

Figure 1-88

1-192

Change 6

T.O. 1F-4C-34-1-1

1-M91-1)

SUU-2SA/A HARE DISPENSER

- : ---

WEIGHT, EMPTY . . .

• 121 Pounds

WEIGHT,FULL . . .

• 340 Pounds

LENGTH.

• 8 Feet

DIAMETER ....

. 13.9 Inches

SUSPENSION LUGS .

. 14.0 Inches

FLIGHT LIMITS . . .

. Refer to Flight Manual

EXPLOSIVE

BOLTS

Figure 1-89 (Sheet 1 of 2)

Change 3

1-193

SVU-25B/A, C/A HARE DISPENSERS Hp

3.9

157 Pounds
360 Pounds
8 Foot

13.9 Inchos

Refer to Flight Manual

DISPENSER DRAG INDEX
WEIGHT EMPTY . . .
WEIGHT FULL ....

LENGTH .

DIAMETER .

FLIGHT LIMITS . . .

11 )

Figure 1-90

| on Mod 4 or LUU-l/B,-5/B,-6/B markers. During
loading, the controls are removed from their SAFE
positions and set on a specific time value (in sec-

I onds). A connecting lanyard is installed between
each pair of flares or markers, and during ejection,
tension on the lanyard initiates the flare or marker
fuze train. The two flares or markers are approxi¬
mately 150 feet apart at flare ignition.

SUU-25B/A FLARE DISPENSER

The SUU-25B/A flare dispenser is capable of dis¬
pensing eight MK 24 or LUU-2/B flares or eight
LUU-1B, -5/B, -6/B markers, (figure 1-90). The
equipment is designed to be returned and used for
more than one mission. The dispenser consists of a

Change 5 1-194A/(1-194B blank)

T.O. 1F-4C-34-1-1

center section constructed of four metal tubes en¬
closed by an outer skin with metal bulkheads on each
end. A suspension lug reinforcement plate (strong
back) is installed at the top of the center section.
Flares/markers are loaded against a compression
cushion and are held in place by a retaining link and
shear pin. Inpulse cartridges are loaded in the
breech assembly at the forward end of each tube.

Two electrical receptacles, on top of the center sec¬
tion, permit electrical connection of the dispenser
to the aircraft. However, only one receptacle is
connected for dispenser operation. Each receptacle
is equipped with a shorting button which may be
positioned to safe the dispenser electrical circuit.
This button is removed from the applicable recep¬
tacle before installing the dispenser on the aircraft.
This dispenser has no single/ripple mode switch;
the intervalometer sequences to fire one tube at a
time.

SUU-25C/A FLARE DISPENSER

The SUU-25C/A flare dispenser is capable of dis¬
pensing eight MK 24 type flares or flare markers.
Single flare dispensing is the primary feature; i.e.,
the dispenser intervalometer causes one flare to be
dispensed with each release pulse. Each of the four
tubes has two breech assemblies loaded with an im¬
pulse cartridge. One breech is routed to a chamber
between the forward and aft flares. The aft flare is
dispensed first by cartridge gases creating a tem¬
porary compression chamber between the flares.

Eight shear pins are used to retain each flare, four
are located in the center section of the dispenser and
four in the aft end. All other features of the SUU-

25C/A dispenser are the same as the SUU-25B/A
dispenser.

LUU-l/B, -5/B, -6/B TARGET MARKER
FLARES

The LUU-l/B, -5/B, -6/B target marker flare is
4.87 inches in diameter, 36 inches long, and weighs
26 pounds. The only difference between the three
flares is the color of the flame: the LUU-l/B burns
red, the LUU-5/B burns green, the LUU-6/B burns
fuchsia. These are MK 24 Mod 4 illumination flares
with a different candle/parachute assembly installed.
The candle is designed to burn for 30 minutes on the
ground providing an easily distinguished red/green/
fuchsia colored flame. It is intended that the color
be distinguishable in the presence of burning illumi¬
nation flares.

The candle is inverted (the burning surface ignites
on the end connected with the parachute) to reduce
the changes of snuffing out the flame on ground im¬
pact. The cast candle is 27 inches long, 4 inches
in diameter, and weighs 19 pounds, with 16 pounds
of flare composition.

A steel suspension cable links the parachute and the
wooden suspension block on the bottom of the candle.
The suspension cable passes through the center of a
2.75-inch diameter protective core in the center of
the candle. The suspension cable extends 6 feet from
the top of the candle to a point where it is connected
to eight 6-foot shroud lines.

The parachute for the target marker flare is a
cruciform design, which utilizes 7.5 x 2 foot panels

Change 5

1-195

T.O. 1F-4C-34-1-1

sewn together in the form of a plus sign. The para¬
chute is designed to provide a 30 foot per second rate
of descent before flare ignition and to snag in the top
of heavy foilage, making it useful in jungle areas.
After flare ignition the flare has a rate of descent of
approximately 15 feet per second.

The 5-to-30-second delay ejection fuze and the 10-
to-30-second delay ignition fuze from the MK 24 il¬
luminating flare are used for the target marker
flares. Since the ignition of the candle takes place
at the end opposite to the ignition fuze, a double ply
quickmatch train is coiled inside the ignition fuze
cavity and threaded through the protective center
core of the candle. The quickmatch is extended into
the cavity and is coiled over a hot-burning material
called the first fire mixture. The candle has a 1/8-
inch coating of the first fire mixture. Formed in the
candles are two 1/2-inch diameter by 3-inch long
holes filled with a first fire mixture having a 2-min¬
ute burn time which increases the capability of the
burning candle to withstand ground impact and con¬
tinue burning.

I Standard MK 24 launchers and launching procedures
can be used to launch the LUU-l/B, -5/B, -6/B
target marker flares. The ejection and ignition fuzes
must be set before launching. Upon launching, the
pull on the lanyard ignites the ejection fuze. At the
conclusion of the ejection fuze delay, an ejection
charge expels the candle and parachute from the
outer case. The ejection charge also ignites the
ignition fuze delay element which in turn ignites the
candle.

LUU-l/B, -5/B, -6/B FLARE DELIVERY

The level release tables for the LUU-l/B flare pre¬
sented in T.O. 1F-4C-34-1-2 are applicable to the
LUU-5/B, -6/B flares. The level release tables pro¬
vide the horizontal travel and vertical drop prior to
flare ignition fuze settings. During mission planning
a release altitude, an ejection fuze setting, and an
ignition fuze setting must be selected which assures
flare ignition prior to ground impact. The total time
of fall is the sum of the ejection fuze setting plus the
ignition fuze setting plus the time of fall after flare
ignition based on a rate of descent of 15 ft/sec. For
determining wind corrections in feet per knot of wind,
multiply the total time of fall in seconds by 1.7.

LUU-2/B FLARE

The LUU-2/B flare is a pyrotechnic illuminating de¬
vice with a 4.5-minute burn time. The flare weighs
approximately 30 pounds and is identical to the
MK 24 flare in external dimensions.

Prior to placing the flare into the launcher, the de¬
sired free fall distance in feet (delay time) must be
set into the timer. This is done by turning the knob
in the center of the timer cover clockwise until the
pointer is opposite the number of feet desired. The
available settings are 500, 1500, 3000, 4500, 6000,
7500, 9000 and 10,500 feet. However, tests have
indicated that settings of 7500, 9000, and 10,500

result in vertical fall of 6500, 7500 and 8500 feet
respectively.

The timer knob will be removed by the launcher as the
flare is ejected through the launcher. Removal of the
timer cover pulls the timer knob which starts the
timer. After the selected delay time, the release
mechanism is tripped allowing the timer and cover
to be ejected from the flare case by a spring. As the
timer is ejected, it pulls the parachute with it. De¬
ployment of the main parachute produces the shock
force on the support cables through the ignition lan¬
yard to rotate a bellcrank in the ignition system,
shearing a safety pin and cocking and releasing a
firing pin. The firingpin strikes and initiates aprimer
which ignites boron pellets. The boron pellets ignite
a wafer of propellant which ignites the flare candle.
Pressure buildup on flare ignition blows out pressure
relief plugs in the igniter housing after which the
flare case burns through, and the ignition housing
falls free.

The flare burns for approximately 270 seconds. At
candle burnout, an explosive bolt is initiated which
releases one parachute support cable causing the
parachute to collapse.

MK 24 MOD 4 FLARE

The MK 24 Mod 4 flare is contained in a cylindrical
aluminum outer case that is 4.8 inches in diameter
and 36 inches long. The Mod 4 flare weighs approxi¬
mately 27 pounds. The parachute and candle are
hermetically sealed inside the outer case by a fuze/
timer assembly at one end and a shear plate at the
other end. Two mechanical timers control the ejec¬
tion and ignition sequence. The Mod 4 flare does not
have a 5-second setting on the ignition timer. Delays
are selected by positioning color coded dials on the
fuze end of the flare (figure 1-89) after removing the
thumb screw which locks the dials in the safe posi¬
tion. The ejection and ignition sequence is initiated
by a 12-pound pull on the braided steel lanyard that
is threaded through the center of the settable dials.
The cable separates from the flare with a pull of
50 pounds. Caution should be exercised when handl¬
ing the flare regardless of the status of the fuze,
safe or armed, as a 12-pound pull will always func¬
tion the fuze and render the flare useless if it were
safe, or a fire hazard if it were armed. Two MK 24
flares are j oined by hooking the fuzing lanyards to¬
gether. When the flares are ejected from the dis¬
penser into the slipstream, aerodynamic forces
cause sufficient pressure to separate the fuze lan¬
yard from one of the flare canisters, activating both
fuze timers in the process. The parachute and can¬
dle are ejected from the outer case when the ejection
delay time is elapsed. The ejection delay time per¬
mits the flare to decelerate prior to parachute de¬
ployment Deceleration is required to prevent para¬
chute failure at high release speeds. The ignition
timer is actuated at parachute deployment Upon
completion of the ignition time delay, the candle is
ignited. The descent of the flare during the ejection

1-196

Change 5

T.O. 1F-4C-34-1-1

DRAG INDEX.

.1.9

WEIGHT.

.154 Pounds

LENGTH.

.63.0 Inches

DIAMETER.

.8.25 Inches

SUSPENSION LUGS.

.14.0 Inches

BALLON DIAMETER.

.20 Inches

OUTPUT, CANDLEPOWER.

.5 Million

BURN TIME.

.5 Minutes

VERTICAL FALL DURING BURN . . .

. 1500 Feet

FLIGHT LIMITS.

. . . Refer to Flight Manual

F 4-34-1.437

Figure 1-91

delay time is approximately 200 feet per second;
during the ignition delay time, approximately 15 feet
per second; after flare ignition, approximately 7.5
feet per second. The actual time that the flare re¬
mains suspended after ignition and after burnout is
a function of the altitude at time of ignition, the
amount of hot air captured under the parachute can¬
opy, and the air currents. Refer to the SUU-25A/A,
-42/A Flare Dispensing bombing table, T.O. 1F-
4C-34-1-2.

MLU-32/B99 FLARE (BRITEYE)

v,_. The MLU-32/B99 flare (figure 1-91) is a five mil¬

lion candlepower pyrotechnic illuminating device
which burns for 5 minutes. A 19-foot diameter hot
air balloon is used to achieve a descent rate of 3 fps.
A preburnout (red) warning signal is ignited during
the last 30 seconds of burning. The flare has a me¬
chanical timer instead of a fuze, a heat generator to
provide the desired thermodynamic properties to the
balloon, and a lift destruct system initiated upon
completion of flare burning. The flare is externally
carried and suspended from the MER and TER.

The flare produces approximately 0.4 foot candles of
illumination on the combat area. This compares to
approximately 20 times full moon light.

When the flare is released from the MER/TER, the
flare timer is initiated by the withdrawal of the arm¬
ing wire. The adjustable timer provides a minimum
delay of 2 seconds (and a maximum of 20 seconds)
for safe aircraft separation. After completion of the
selected time interval, the timer mechanically
initiates an explosive bolt. Separation of the bolt al¬
lows the clamp assembly to release the two halves of
the outer case. Internal compression springs in the
case sections assist the separation of the inner flare
assembly from the outer case sections.

As the forward outer case section separates from the
inner flare assembly, the drogue chute is deployed.
The initial jerk on the drogue chute suspension line
initiates the pyrotechnic delay reefing line cutter.
During the 3 second delay of the reefing line cutter,
the inner flare assembly is decelerated to a safe
balloon deployment speed. Upon completion of the
delay, the drogue chute strips the deployment case
off to deploy the balloon. Completion of balloon in¬
flation tensions the internal Y-bridle which in turn
mechanically initiates the flare igniter. The flare
igniter directs an intense, short duration flame on
the surface of the candle and heat generator, igniting
both.

The high temperature gases from the ignited candle
burn through the thin aluminum ring thus allowing the

1-197

T.O. 1F-4C-34-1-1

WEIGHT EMPTY. 384 Pounds

LENGTH.11 Feet, 8 Inches

DIAMETER.23 Inches

SUSPENSION LUG DIST., . . . 30 Inches

NO. OF TUBES.8 Tubes (2 Flares or markers per tube)

PAYLOAD.MK 24 Mod 4, LUU-2/B Flares or LUU-l/B, -5/B, -6/B Markers

FLIGHT LIMITS.Refer to Flight Manual

Figure 1-92

4C-34-l-l-(94)

candle to tip over (rotate) and play out the suspension
cable which is housed in the base of the candle. The
burning face of the candle faces the ground when the
flare system is fully deployed.

The MLU-32/B99 level release table T.O. 1F-4C-
34-1-2 provides the flare horizontal travel and verti¬
cal drop from release to ignition for the range of
available timer settings (2 - 30 seconds). Since the
flare will fall approximately 1500 feet during the 5-
minute burn time, the vertical drop for the selected
timer setting must be increased at least 1500 feet to
determine a release altitude which will assure flare
burn-out prior to impact.

SUU-42/A FLARE DISPENSER

The SUU-42 dispenser (figure 1-92) is a single car¬
riage unit mounted directly on the outboard arma¬
ment pylons for carriage on the outboard wing sta¬
tions. The dispenser is modified to carry the MK 24
Mod 4 flares, the LUU-l/B, -5/B, -6/B markers
or the LUU-2/B flares. The LUU-l/B, -2/B, -5/B,
-6/B, is identical in dimensions to the MK 24 Mod 4
flare.

The SUU-42 dispenser has eight ejection tubes that
can carry two flares (markers) per tube. The flares
are ejected from the tail section of the dispenser
when the bomb button is depressed. A safety pin is
installed in each dispenser to prevent accidental dis¬
charge during ground operations. The dispenser has
a ground settable intervalometer with settings from
0.01 to 9.99 seconds. Three knobs are settable in
increments 0.01, .10, and 1.00 seconds with a lowest
reliable setting of 0.10 second. The dispenser also
has a selector switch with positions of MANUAL and
RIPPLE. With the weapon selector knob in the cock¬
pit positioned to RKTS & DISP/SINGLE and the SUU-
42 selector switch in MANUAL, a single flare is re¬
leased from the dispenser for each actuation of the
bomb button. With the SUU-42 selector switch in
RIPPLE, continuous bomb button voltage (bomb but¬
ton depressed) releases the flares at a rate deter¬
mined by the dispenser intervalometer. With the
weapon selector knob in RKTS & DISP/RIPPLE, the
SUU-42 selector switch must be set to MANUAL. In
this case, continuous bomb button voltage (bomb
button depressed) is directed to the aircraft inter¬
valometer where a release pulse is alternately de¬
livered to each selected station at the rate deter¬
mined by the interval switch.

1-198

Change 5

ill

T.O. 1F-4C-34-1-1

LAU-3/A ROCKET LAUNCHER

AFT VIEW

4 C—34— 1 — 1 —(95)

Figure 1-93

Note

The weapon selector knob is normally po¬
sitioned to RKTS & DISP/SINGLE for dis¬
pensing flares from the SUU-42. However,
if the SUU-42 selector switch is set to MAN¬
UAL, the weapon selector knob may be posi¬
tioned to RKTS & DISP/RIPPLE if a ripple
release is desired.

LAU-3/A ROCKET LAUNCHER

The LAU-3/A rocket launcher (figure 1-93) carries
and launches nineteen 2.75-inch folding fin aircraft
rockets. The flight configuration consists of the
loaded center-section assembly with streamlined
fairings installed and locked onto the ends. When the
launcher is fired, the front fairing is shattered by
rocket impact, and the tip of rear fairing is shattered
by rocket blast. The frangible fairings are made of
treated paper and shatter readily after the rocket im¬
pact and blast. When attached, the fairing is flush
with the outside surface to provide an aerodynami-
cally smooth joint. Approximately 11 inches of the
base of the rear fairing will remain on the adapter to

channel rocket debris away from the undersurface of
the wing. The launcher center section is constructed
of 19 paper tubes clustered and bonded together to
form an integral part of the structure and wrapped
with a thin aluminum outer skin. Detent devices
within the tubes restrain the rockets against normal
flight loads and provide electrical contact to ignite
the rockets. Contact fingers on the aft bulkhead pro¬
vide a ground to complete the circuit through the
rockets. Two receptacles on top of the center sec¬
tion provide the connection to the aircraft rocket¬
firing circuitry. These receptacles are wired in
parallel; therefore, only one of them is connected to
the aircraft. A shorting pin is inserted in the side
of the LAU-3/A launcher. The shorting pin is a
ground safety device which is removed prior toflight.
Electrical power for the rocket ignition system is
supplied to the launcher by the 28 volt dc armament
circuit of the aircraft. The burn-out, wire type in-
tervalometer, located within the LAU-3/A launcher,
converts the aircraft firing voltage into a ripple fire
pulse with a 10-millisecond delay interval. The rockets
will ripple fire in pairs until the launcher isempty. The
launcher should completely fire-out in approximately
0.1 second. The switch on the MER and TER must be

Change 7

1-199

T.O. 1F-4C-34-1-1

positioned on ROCKET to provide the ripple fire se¬
quence. Aircraft firing voltage is routed through a
resistor to limit the voltage applied to the interval-
ometer. If the switch is in the CBU position, the
resistor is bypassed. This would cause the high
voltage to burn out the wire type intervalometer at a
rate that will produce a near salvo fire effect: the
rockets will collide upon leaving the launcher.

Note

There are several intervalometers available
for use with the LAU-3/A; some are reus¬
able. The burn-out unit supports the ripple
fire mode only. The reusable type support
both the ripple and single-fire modes, and
include a reset switch to select the firing
modes. In a singles mode, two rockets are
fired with each fire pulse.

struction. The LAU-68A/A is approximately 10
inches longer than the other 7-tube launchers to
accomodate a longer warhead. Refer to figure 1-95
for ripple fire rate of each launcher.

The rocket launchers carry and launch seven 2.75-
inch folding fin aircraft rockets. The flight configu¬
ration consists of the loaded center-section assem¬
bly with streamlined fairings installed and locked
onto the ends. When the launcher is fired, the front
fairing is shattered by rocket impact, and the rear
fairing is shattered by rocket blast. The frangible
fairings are made of an impregnated molded fibre,
designed with a waffle type structure which is shat¬
tered readily by the impact of the rocket. The aft
fairing is molded in two sections, such that the
rocket blast shatters the center portion while the
base section remains to act as a funnel to direct de¬
bris away from the aircraft. When attached, the
fairing is flush with the outside surface to provide an
aerodynamically smooth joint.

WARNING

The ROCKET harness (blue) and the CBU har¬
ness (yellow) appear to be identical; the har¬
ness marked ROCKET must be used. If the
CBU harness is inadvertently used, stray
voltage might cause the launcher to salvo
fire when aircraft power is applied if/when
the weapons selector knob is positioned on
RKTS & DISP with the armament safety over¬
ride IN or the landing gear handle UP; the
MA switch need not be in ARM, nor the bomb
button depressed for this to happen. If the
rocket launcher does not fire by stray volt¬
age, it will not fire under normal select and
fire conditions; the launcher should be re¬
leased prior to landing.

LAU-32, -59, -68 ROCKET LAUNCHERS

The LAU-32A/A, -32B/A, -59/A, -68A/A rocket
launchers are illustrated in figure 1-95. The LAU-
32A/A is the combat model which is normally re¬
leased after the seven 2.75-inch rockets have been
fired. The main differences between the launchers
are that the LAU-32B/A, -59/A, -68A/A are re¬
usable rocket launchers that have aluminum launch¬
ing tubes (instead of paper), an intervalometer which
is adjustable and reusable, and a selectable option of
SINGLE fire or RIPPLE fires. The LAU-59/A, as
it differs from the LAU-32B/A, is of heavier con¬

The launcher center section is constructed of seven
paper tubes clustered and bonded together to form an
integral part of the structure and wrapped with a thin
aluminum outer skin. Detent devices within the tubes
restrain the rockets against normal flight loads and
provide electrical contact to ignite the rockets. Con¬
tact fingers on the aft bulkhead provide a ground to
complete the circuit through the rockets. Two re¬
ceptacles on top of the center section provide the
connection to the aircraft rocket-firing circuitry.
These receptacles are wired in parallel; therefore,
only one of them is connected to the aircraft. LAU-
59 and LAU-68A/A launchers have a shorting pin in¬
stalled which is removed prior to flight. Electrical
power for the rocket ignition system is supplied to
the launcher by the 28 volt dc armament circuit of
the aircraft. The burnout, wire type intervalometer,
located within the LAU-32A/A launcher, converts
the aircraft firing voltage into a ripple fire pulse
with a 10-millisecond delay interval. The rockets
will ripple fire until the launcher is empty or the
bomb button (pickle button) is released. The LAU-
32 A/A launcher should completely fire-out in approx¬
imately 0.07 second. The LAU-32A/A intervalom¬
eter is the same, and interchangeable with the LAU-
3 / A launcher.

The LAU-32B/A, -59/A, -68A/A launcher has an
adjustable intervalometer located on the aft bulkhead.
The intervalometer dial has the following positions;
LOAD, ARM, and 1-2-3-4-5-6-7. To select a par¬
ticular tube for firing, set the intervalometer dial
on the preceding tube )e.g. to fire tube 5 set dial on
tube 4). The LOAD position is electrically safe. Be¬
fore installing the aft fairing, the dial is moved

1-200

Change 7

Figure 1-94 deleted

T.O. 1F-4C-34-1-1

r-'

LAU-32,-59/A-68A/A ROCKET LAUNCHER

SINGLE FIRE OPTION...

REUSABLE.

RIPPLE RATE.

WEIGHT, EMPTY.

WEIGHT, FULL.

LENGTH.

DIAMETER.

LAU-32A/A

0.010 Sec

41.5 Lbs
164 Lbs
67 In
10 In

LAU-32B/A

YES

0.020 Sec

51.5 Lbs
174 Lbs
67 In
10 In

LAU-59/A

YES

0.020 Sec
56.0 Lbs
184 Lbs
62 In
10 In

LALM8A/A

YES

0.060 Sec
67 Lbs

217.5 Lbs
72.63 In
9.8 In

SS4C-34-l-1-<971

Figure 1-95

counterclockwise to the ARM position. The LAU-
32B/A, -59/A, -68A/A has an option selector
switch, located at the top of the aft bulkhead, with
two positions: one position is RIPPLE and the other
is SINGLE. The selection is made prior to installa¬
tion of the aft fairing.

The switch on the MER and TER must be positioned
on ROCKET. Aircraft firing voltage is routed
through a resistor to limit the voltage applied to the
intervalometer. If the switch is in the CBU position,
the resistor is bypassed. This will cause the high
voltage to operate the intervalometer at a rate that
will produce a near salvo fire effect; the rockets will
collide upon leaving the launcher.

WARNING

The ROCKET harness (blue) and the CBU
harness (yellow) appear to be identical; the
harness marked ROCKET must be used. If
the CBU harness is inadvertently used, stray
voltage might cause the launcher to salvo
fire when aircraft power is applied if/when
the weapons selector knob is positioned on
RKTS & DISP with the armament safety over¬
ride IN or the landing gear handle UP. The
master arm switch need not be in ARM, nor
the bomb button depressed for this to happen.
If the rocket launcher does not fire by stray
voltage, it will not fire under normal select

and fire conditions; the launcher should be
released prior to landing.

2.75-INCH FOLDING FIN AIRCRAFT
ROCKET

The 2.75-inch folding fin aircraft rocket (FFAR) (fig¬
ure 1-96) is designed to provide air-to-ground arma¬
ment for tactical aircraft. The rocket can be config¬
ured with various rocket heads (warheads) and fuzes
to accommodate the tactical requirement; high-ex¬
plosive (HE), anti-tank (HEAT), fragmentation
(pearlite malleable iron, PMI), flechette (steel
darts), or a plaster-loaded inert head used for prac¬
tice (figure 1-96). The rocket motor tube is made of
seamless aluminum alloy tubing and is 32 inches
long. The rocket motors are designated MK 4 Mods 0
thru 8. The propellant used is an internal burning
grain ballistite. The burning rate of the propellant
varies with temperature, from 2.92 seconds at -50°F
to 1.42 seconds at 130°F. The propellant grain in
rocket motors MK 4 Mods 0, 1, 2, and 3 is sensitive
to temperature change. The propellant grain used
in rocket motors MK 4 Mods 4, 5, 6, 7 and 8 is relative¬
ly insensitive to temperature change. The rocketmo-
tor is ignitedby aircraftelectricalpowerthrough an
igniter. An electric squib ignites the mixture of
black powder and magnesium powder contained
in the igniter. The igniter is located at the for¬
ward end of the rocket motor in the head closure
of the motor assembly. The rocket nozzle/fin
assembly, which attaches to the rear end of the
motor tube, consists basically of a nozzle plate,

Change 5

1-201

T.O. 1F-4C-34-1-1

CONTACT DISK

INCH

FOLDING

FIN

AIRCRAFT ROCKET

CONTACT
LEAD WIRE

FOLDING FIN AIRCRAFT ROCKET (FFAR)

WEIGHT:.18 to 22 POUNDS

LENGTH.48 to 55 INCHES (FINS FOLDED)

DIAMETER:.2.75 INCHES

4C-34-1-M98)

Figure 1-96

four nozzles, a fin actuating mechanism, four folding
fins, and a fin retainer and contact disc. Gas pres¬
sure from the motor operates the piston and cross
head, pushing the heels of the fins and thereby caus¬
ing the fins to open. The cross head remains in its
rearmost position and is effective in locking the ex¬
tended fins in their normal angular projection rear¬
ward against the force exerted by the airstream even
after loss of external pressure at motor burn-out.

The fins are shaped aluminum alloy plates, 6.5-
inches long and 1.26-inches wide. When folded, they
extend to the rear within the 2.75-inch diameter of
the round.

For use of 2.75-inch FFAR on F-4 aircraft
or in the SUU-20/A dispenser, only the plas¬
tic type fin retainer or contact disc without
metal picture frame are approved. To use
the contact disc without metal picture frame,
it is necessary to hold fins closed or in
folded position with tape.

2.75-INCH ROCKET WARHEADS

MK 1 WARHEAD (HE)

The MK 1 high explosive (HE) rocket warhead (figure

1-97) is 11.1-inches in length and weighs 6.47 pounds

with fuze installed. The warhead is loaded with 1.4
pounds of HBX-1 high explosive for blast, fragmen¬
tation, mining or demolition effects. The high explo¬
sive (HE) head uses the MK176, MK178 or M427point
detonating fuze. The M178 fuze would allow the war¬
head to penetrate for internal blast and mining,
whereas the M427 fuze would provide a surface burst.
The inert warhead has the same configuration and
carries an inert load of plaster and a dummy fuze.

MK 5 WARHEAD (HEAT)

The MK 5 (HEAT) warhead has the same dimensions
and weight as the HE warhead. All models of the
HEAT warhead are designated MK 5. The MK 5 war¬
head is constructed with a shaped charge for pene¬
tration of armored vehicles, tanks, and other resis¬
tant targets. The length and weight with the MK 181
base detonating fuze installed is the same as the HE
head. The HEAT head is loaded with 0.89 pound of
composition B and with a shaped charge for penetra¬
tion of armored or other resistant targets. The
shaped charge is designed to focus all the energy of
the detonation into a narrow, high velocity jet. At
impact, the base detonator (located at the base of the
fuze) is ignited to detonate the explosive charge. The
shock waves of the detonation move forward from the
base toward the apex of the thin metal liner that

1-202

Change 5

T.O. 1F-4C-34-1-1

2.75-INCH FFAR WARHEADS and FUZES

FUZE CAVITY
LINER —

BRAZING
GROOVE•

DETONATOR

DELAY ELEMENT

ROTOR

DETONATOR

TIMING MECHANISM

TIMING GEAR

PRIMER

ROTOR

BOOSTER CUP

FLASH TUBE

DIAPHRAGM

MK5 Warhead (HEAT) and MK181 Fuze
(Paint Initiation-Base Detonation)

SHAPED CHARGE
BOOSTER

DETONATOR

DETONATION
WAVES —'

PRIMER

BASE DETONATING
ELEMENT—,

WINDSHIELD

MK 5 WARHEAD

FLASH TUBE

Shaped Charge Warhead

F4-34-I-470.1

2.75 COMPONENTS

2.75" Rocket Motor MK 4 Mods 0 thru 8

FUZE

WARHEAD

WDU-4A/A

WDU-4A/A (FLECHETTE)

M427 Mods 0, 1

M151 (PM1 or WP)

MK 176 Mods 1, 2

MK 1 Mnrl< 1 ? 4 <5

MK 178 Mods 0, 1, 2

MK 181 ModO

MK 5 Mod 0 (HEAT)

Figure 1-97 (Sheet 1 of 2)

FUZE CAVITY
LINER-

COMP B4

PUSHER PLATE

FLECHETTE

T.O. 1F-4C-34-1-1

FUZES

WARHEADS

INCH

FEAR

2.75

- (CONTINUED)

COMP B4 BURSTER CHARGE

M15G Warhead (WP>
(White Phosphorus)
and M421 Fuze

WHITE PHOSPHORUS

WDU-4A/A FUZE
OPERATING SEQUENCE

SPLIT SLEEVE

GROOVE

FUZE ASSY

W0U-4A/A Warhead
(Flechetie) and Fuze

EJECTION

HARGF

T.O. 1F-4C-34-1-1

forms the concaved cone at the front of the shaped
charge. (The strong outer shell of the shaped charge
is not shattered by the detonation.) Collapse of the
thin metal liner starts at the apex of the cone. As
the liner collapses, it ejects a narrow jet of explo¬
sive products and metal particles at extremely high
velocities. The jet is first to strike the target, fol¬
lowed by the main body of the cone, referred to as
the secondary penetration or the slug. When the jet
strikes in target, pressures up to 250, 000 pounds
psi are produced at the point of impact. The depth of
jet penetration is a function of the target density
rather than strength. There is no appreciable lateral
blast effect or temperature rise produced by the
shaped charge, since all the energy is directed for¬
ward.

M 151 WARHEAD (PMI)

The M151 warhead has a pearlite, malleable iron
(PMI) case designed to produce high fragmentation.
The warhead is employed as an air-to-ground, anti¬
personnel and anti-material weapon. The warhead is
2.75 inches in diameter, approximately 15 inches in
length, and weighs 9.4 pounds with the M427 super¬
quick fuze installed. The warhead is loaded with 2.37
pounds of Comp B-4 explosive for fragmentation and
blast effect. The superquick fuze, greater length of
warhead, and improved fragmentation break-up of
the PMI case combine to provide more than twice the
effectiveness of the standard HE warhead.

M 156 WARHEAD (WP)

The M156 warhead filled with 2.13 pounds of White
Phosphorus (WP) has the same external shape as the
M151 (PMI) warhead. A bursting tube containing
three ounces of Comp B-4 is inserted through the
center axis of the warhead. The explosive tube is
detonated upon impact by the M427 fuze to cause dis¬
persion of the White Phosphorus.

White Phosphorus (WP) is a yellow, wax-like sub¬
stance that melts at 111°F. The most characteristic
property of WP is spontaneous ignition when exposed
to air, burning with a yellow flame and giving off a
large volume of white smoke. The smoke in field
concentrations is not toxic; however, the fumes are
toxic.

If white smoke is detected arising from a
leaking warhead, there is an immediate dan¬
ger of fire.

WDU-4A/A WARHEAD (FLECHETTE)

The WDU-4A/A warhead is a flechette (miniature
steel dart) anti-personnel warhead. The WDU-4A/A
warhead is 2.75 inches in diameter, 17.76-inches
long, weighs 9.4 pounds, and contains a base fuze,
ejecting charge, piston, 2200 20-grain flechettes,
and an aerodynamic nose cone (figure 1-97 sheet 2).

The WDU-4A/A warhead is compatible with all 2.75-
inch FFAR motors and launchers. The fuze is in¬
stalled during assembly and is an integral part of the
warhead. At launch, acceleration forces arm the
fuze. At motor burn-out (approx. 1.8 sec. after
launch), an airburst is initiated by the deceleration
forces which frees the spring loaded firing pin to
ignite the M9 ejecting charge. The M9 ejecting charge
generates a gas pressure against the pusher plate
(piston) which transmits the pressure through the
stacked flechettes and to the shear pins on the nose
cone. The shear pins are broken to allow the nose
cone to be ejected, followed by the flechettes. The
flechettes are packed tightly in the split sleeves with
alternating flechettes pointing fore and aft. When the
flechettes are ejected, aerodynamic forces cause the
tail-forward flechettes to tumble and streamline; this
weathervaning causes dispersion. Slant range at
launch is a factor in determining the slant range at
rocket motor burn-out, and therefore, is a critical
factor in determining the dispersion and weapon ef¬
fectiveness. Refer to the rocket launch table for
flechette warhead ballistics, T.O. 1F-4C-34-1-2. Re¬
fer to the Confidential manual T.O. 1F-4C-34-1-1A,
Supplementary Data, for the planning charts used to
determine impact pattern size and optimum launch
conditions.

2.75-INCH ROCKET FUZES

MK 176 FUZE (PD)

The MK 176 fuze is a cone-shaped, steel constructed
point-detonating, delay, nose fuze. The fuze is det¬
onator-safe and is armed when the sustained accel¬
eration of the rocket motor overcomes the force of
the anti-setback springs that restrain the weight of
the fuze arming mechanism. The rate of accelera¬
tion required for arming is approximately 20 Gwhich
insures that the rocket will travel at least 500 feet
before the fuze arms. The maximum distance al¬
lowed for arming is approximately 1400 feet. The
fuze contains the firing mechanism, arming mecha¬
nism, primer, delay element, detonator, lead and
booster. The delay element provides a 0.0003 sec¬
ond delay. The fuze is threaded at the lower end for
attachment to the HE or PMI warheads.

MK 178 FUZE (PD)

The MK 178 fuze is similar to the MK 176 fuze in
every respect except that the delay element between
the primer and the detonator has been removed and
replaced by a flash tube to reduce fuze function time.
The production model is designated Mod 2.

M 427 FUZE

The M427 fuze provides a superquick, graze sensi¬
tive fuze that will provide warhead detonation above
ground to increase the fragmentation produced by the
M151 warhead. The M427 fuze is also used with the
White Phosphorus filled M156 warhead. The M427
fuze is detonator-safe, employing a detonator-out-of-
line rotor that is brought into alignment by the G
forces of rocket motor acceleration. The detonator-
safe mechanism installed in the M427 is basically

Change 5

1-205

T.O. 1F-4C-34-1-1

the same as that installed on the MK 176/178, re¬
quiring 20 G for approximately 1 second to complete
the arming sequence. This provides a minimum of
500 feet, to a maximum of 1200 feet of safe travel
before the warhead is armed. The M427 fuze will
function instantaneously without ricocheting off hard
ground or burying in a soft mud or water. The front
of the fuze contains a striker plate which centers an
auxiliary striker pin over the firing pin. The striker
plate transmits any backward vector force to the fir¬
ing pin to assure reliable functioning at low impact
angles (approximately 3 degrees).

MK 181 FUZE (POINT INITIATING-BASE
DETONATING)

The MK 181 fuze is used exclusively with the HEAT
warhead (shaped-charge). The M181 fuze contains a
shaped-charge booster that directs a jet of hot gas
rearward to the base of the HEAT warhead to initiate
the booster pellet which in turn initiates the main
charge of the HEAT warhead. Upon impact, the
shaped-charge booster is initiated. The booster is
concaved at the base to direct a jet stream through
the apex of the HEAT shaped- charge and flash tube to
ignite the booster pellet located at the base of the
warhead. The booster pellet in turn ignites the HEAT
shaped-charge to produce a greater jet in the oppo¬
site direction. This design is to achieve faster fuze
functioning, thereby increasing overall efficiency of
the shaped-charge HEAT head. The arming mecha¬
nism of the MK 181 Base-Detonating fuze is similar
to MK 176/178 fuze arming mechanism. The fuze is
detonator-safe and is armed by sustained accelera¬
tion of approximately 20 G. This insures that the
rocket will travel at least 400 feet before the fuzes
arm. The maximum distance for arming is approxi¬
mately 1400 feet.

WDU-4A/A FUZE (FLECHETTE)

The fuze section (figure 1-97 sheet 2) contains the
same safe and arming mechanism as the MK 176
fuze, with the addition of a metal dowel press fitted
into the rotor. The pin prevents a spring-loaded set¬
back piston from moving forward and releasing the
spring-loaded firing pin. The firing pin is held in
place by a steel locking ball which rests in the
groove of the firing pin. The ball, in turn, is held in
place by a steel spacer pin which rests against the
spring-loaded setback piston. This acceleration-
activated arming mechanism provides a minimum
500 ft aircraft separation before the fuze arms.

When the rocket is fired the acceleration force com¬
presses the spring of the setback piston, moving it
to the rear. This action allows the rotor to move the
dowel pin aft and line up the ignition train in the ro¬
tor with the firing pin. As the rocket acceleration
decreases, just prior to rocket motor burnout, the
spring pushes the setback piston forward, releasing
the pin and ball holding the firing pin. The spring-
loaded firing pin pushes the retaining ball out of the
groove and fires the expulsion charge. The expulsion
charge develops a gas pressure of approximately
1300 psi in the expansion chamber and forces the
pusher plate, flechettes, and hemicylindrical sleeves

forward, shearing the pins holding the nose plate.

As the pusher plate moves forward, the flechettes
and sleeves are pushed out of the main body cylinder
and expelled into the slip stream ahead of the rocket.
The hemicylindrical sleeves keep the flechettes from
dispersing until all have been forced out of the main
body cylinder.

A/B 45Y-1, Y-2, Y-4 SPRAY TANKS

The spray tanks currently available for carriage in¬
clude the expendable A/B 45Y-1 (liquid agent), the
reusable A/B 45Y-2 (dry agent), and the reusable
A/B 45Y-4 (dry agent) low drag spray tanks (figure
1-98). The tanks are single carriage units mounted
directly on the armament pylon for carriage on the
outboard wing stations.

Note

Loading configuration and authority to carry
these spray tanks must be obtained from
T.O. 1F-4C-1.

LIQUID AGENT

The liquid agent in the Y-l tank is a biological agent
and is considered very toxic. Information concern¬
ing safety requirements, will be supplied later.

A/B 45Y-1 LIQUID AGENT SPRAY TANK

The spray tank is basically a laminated fiberglass
shell in 3 sectons enclosing a flexible bladder liquid
reservoir (containing the biological agent), and a
liquid control and spray system. For cold weather
operations, the tank is equipped with heaters to pre¬
vent freezing of the liquid agent. The heaters are
operated from external power by 115 volt ac source.
The tail section of the tank has an X fin configuration.

The A/B 45 Y-1 spray tank has an air storage bottle
which is pressurized to 3000 psi. Discharge of an
explosive squib, when the arm nose tail switch is po¬
sitioned to NOSE & TAIL, sears a metal seal and
pressurizes the bladder to 40 psi through a pressure
regulator. When the bladder is pressurized, the tank
is armed and ready for use.

WARNING

Once arming procedures are complete, the
A/B 45 Y-l spray tank must not be returned
to home base.

Controlled dissemination is accomplished through
the normal bomb release circuits of the aircraft.
Approximately 3 minutes are required for complete
dissemination of the liquid agent. Dissemination is
controlled at the discretion of the AC by pressing the
bomb release button. The AC may dispense all or
part of the load. The spray is disseminated through
a nozzle in tail section of the tank. The tank must be
jettisoned from the aircraft after the liquid agent has
been completely disseminated.

1-206

T.O. 1F-4C-34-1-1

A/B 45Y-1 SPRAY TANK

mt. . ;i

vtf 1 *

srw*

.''■(Cl ; : :■
©1!’ i j

A/B 45Y-4 SPRAY TANK

SAFETY PIN

A/B 45Y-1, LIQUID AGENT SPRAY TANK

DRAG INDEX.

. 4.7

WEIGHT EMPTY.

. 230 Pounds

WEIGHT FULL.

. 760 Pounds

LENGTH.

. 12 Feet, 6 Inches

DIAMETER.

. 17.0 Inches

FIN SPAN("X“ Configuration) .

. 32 Inches

SUSPENSION LUGS.

. 14.0 Inches

FLIGHT LIMITS.

• Refer to T.O. 1F-4C-1

CAPACITY.

.63.5 gal - 529.0 Pounds

DISSEMINATION RATE . . . .

.20 gal/min. - 166 Pounds/Min

A/B 45Y-2, DRY AGENT, SPRAY TANK

DRAG INDEX.4.7

WEIGHT EMPTY. 478 Pounds

WEIGHT FULL. 552 to 784 Pounds

LENGTH.15 Feet

DIAMETER.21.1 Inches

FIN SPAN (Two;lnverted "V" Configuration) 17.7 Inches

SUSPENSION LUGS.14 Inches

FLIGHT LIMITS.Refer to T.O. 1F-4C-1

CAPACITY. 300 Pounds (Maximum)

A/B 45Y-1 SPRAY TANK

ciuTim unn m , m J

» mSSmwtf

SlU t.TY mum >ii nia,« 1

A/B 45Y-4, DRY AGENT, SPRAY TANK

DRAG INDEX.4.8

WEIGHT EMPTY. 495 Pounds

WEIGHT FULL.715 Pounds

LENGTH ..14 Feet, 2 Inches

DIAMETER.20 Inches

FIN SPAN ("X" configuration) . . . 29.5 Inches

FLIGHT LIMITS.Refer to 1F-4C-1

CAPACITY. 230 Pounds

4C—34—1 — 1—O00)

Figure 1-98

Change 5

1-206A/(1-206B blank)

T.O. 1F-4C-34-1-1

DRY AGENT

The dry agent in the Y-2 spray tank uses a powder
for anti-crop purposes. This powder is non-toxic
and is not considered harmful to personnel. The Y-4
spray tank is filled with two compact dry biological
agent slugs.

A/B 45Y-2 Dry Agent Spray Tank

The spray tank consists of three main sections; cen¬
ter, nose and tail. The nose contains a 24 volt dc
battery and a 24 volt dc drive motor. The center
section contains the dry agent, an internal paddle
assembly which is driven by the motor, and the ori¬
fice outlet area. The nose and tail sections are con¬
nected to the center section by bayonet couplings.

The tail section has an inverted V fin configuration.

Inflight operation and control of the spray tank is
conducted through the aircraft conventional weapons

arm and release circuits. The operating principle of
the spray tank is based on the principle that dry ma¬
terials flow as a fluid when mixed with flowing gas.
During operation, ram air directed into the spray
tank agent container mixes with the dry agent and ex¬
hausts it into the slip stream through an orifice area
underneath the tank. Two circuits, the arming cir¬
cuit and the disseminate circuits, are required for
complete operation of the spray tank. The two cir¬
cuits must be energized in proper sequence; an elec¬
trical interlock is provided in the spray tank control
circuits which prevents out of sequence operation.
Energizing the arming circuit, (nose tail arm switch)
causes the agent container to be pressurized by ram
air flow. Aircraft voltage causes the nose cover and
the air inlet valve to open, thus admitting the ram
air. After the agent chamber is pressurized, it is
only necessary to energize the disseminate (bomb re¬
lease) circuit to start delivery of the material in the
spray tank. Energizing the disseminate circuit opens
a discharge valve and supplies power to the motor

Change 5

1-207

T.O. 1F-4C-34-1-1

through a self contained battery. The AC may dis¬
pense all or part of the agent. The system may be
deenergized by placing the Nose Tail arm switch to
SAFE. This closes the nose cover and air inlet
valve. The rate of dissemination is controlled by the
orifice insert which can range in sizes up to 1 inch.
The tank may be returned to base for reloading.

Note

The dry agent is non-toxic and is not con¬
sidered hazardous to personnel. However,
every effort must be made to properly con¬
tain the agent during operations in friendly
territory.

A/B 45Y-4 Dry Agent Spray Tank

The A/B 45 Y-4 spray tank consists of three sec¬
tions: nose, center, and tail. The nose section con¬
tains a nitrogen pressure supply, flow controls, and
a relay system for monitoring tank functions. The
nose section also has a safety switch assembly, con¬
sisting of a safety pin, housing, and switch. The
function of this assembly is to render the tank safe
during ground handling. Just prior to flight, the pin
is removed, enabling the tank to be armed. The cen¬
ter section of the tank contains two agent slugs, a
drive motor and an agent feed mechanism. The tail
section contains a battery and speed control elec¬
tronics. The tail fins on this tank are mounted in the
X configuration. Dissemination of the agent is con¬
trolled through the bomb button circuits. During
dissemination the drive motor moves two pistons
which drive the two dry agent slugs to the center of
the tank. Here, the agent is forced through two ro¬
tating disaggregator plates. These plates break up
the agent which is then mixed with dry nitrogen and
discharged through a ball valve. This valve is housed
in an aerodynamic shroud on the bottom of the spray
tank. The dissemination rate is determined by a
ground setting. The agent may be disseminated at
15 to 60 pounds per minute depending upon the set¬
ting selected. When the tank is empty, the function¬
ing is automatically stopped and an empty indication
is supplied to the front cockpit. The NOSE & TAIL
position on the arm nose tail switch is used to arm
the tank. Continuous bomb button voltage (bomb but¬
ton depressed) controls the functioning of the tank.
The tank may be de-armed by positioning the arm
nose tail switch to SAFE. After the mission is com¬
pleted, the tank can be jettisoned or returned for
decontamination and refilling as directed by the
Commander.

TMU-28/B SPRAY TANK

The TMU-28/B liquid agent spray tank (figure 1-99)
is suspended from the outboard armament pylons and
jettisoned after dissemination of its contents is com¬
pleted.

WARNING

The TMU-28/B liquid agent spray tank con¬
tains VX agent (nerve gas) which is highly
toxic and can cause death to personnel.

Note

Loading configuration and authority to carry
the spray tanks must be obtained from T.O.
1F-4C-1.

The spray tank has four major components: the agent
container, tail cone section, hardback assembly, and
dissemination nozzle (the boom). The hardback as¬
sembly has 30-inch suspension lugs and provides a
surface for forced ejection of spray tank. The tail
cone section is removable and contains electrical
system components. The dissemination nozzle (the
boom) is retracted during flight and extended approxi¬
mately 30 degrees before dissemination of the liquid
agent to prevent contamination of the aircraft. The
agent container is used to hermetically seal the VX
agent in the spray tank. During flight, the agent is
released when the outlet and inlet cutters are deton¬
ated electrically, opening a hole in the aft and for¬
ward end of the container, permitting the agent to
flow through the nozzle into the atmosphere.

The electrical power for the spray tank electrical
system is supplied by the aircraft electrical system
through the umbilical cable. Electrical power acti¬
vates the safety interlock switch, the extension cir¬
cuit of the actuator to lower the nozzle, and fires
the outlet and inlet cutters. The arming pin on the
left side of the tail cone section, is inserted in the
tank safety interlock switch (located within the elec¬
trical control module) to disarm the tank electrical
system during ground handling. A red streamer
(REMOVE BEFORE FLIGHT) is attached to the pull
ring of the arming pin.

PAU-7/A SPRAY TANK

The PAU-7/A tank is a TMU-28/B spray tank (figure
1-99) modified to carry and dispense defoliant agents.
The data in the paragraphs immediately above are
applicable to the PAU-7/A with the following addi¬
tions. The tank is reusable and may be returned to
base after expending the defoliant agent. Secondly,
if the boom does not extend, dissemination of the
defoliant can still be accomplished. During flight,
the defoliant is released when the inlet and outlet
valves are electrically actuated, opening a port in
both the aft and forward ends of the container and
permitting the agent to flow through the nozzle into
the atmosphere. The list below are PAU-7/A excep¬
tions to the physical data shown in figure 1-99.

Weight Full 2300 pounds

Rate of Spray 6 gallons/second

1-208

T.O. 1F-4C-34-1-1

m-28/B, PAU-7/A SPRAY TANKS

PAU-7/A

TMU-28/B

1935 Pounds
567 Pounds
15 Ft, 5.5 Inches
22.5 Inches
34.9 Inches
160.4 Gallons
20 Gallons/Second
Ref. Flight Manual

1935 Pounds
567 Pounds
15 Ft, 5.5 Inches
22.5 Inches
34.9 Inches
160.4 Gallons
6 Gallons/Seconds
Ref. Flight Manual

WEIGHT . . .
WEIGHT EMPTY
LENGTH . . .
DIAMETER . .
FIN SPAN . .
AGENT . . .
RATE OF SPRAY
FLIGHT LIMITS

4C—34 —1—1 —(»01 )

Figure 1-99

Change 5

1-209

T.O. 1F-4C-34-1-1

I? H

FLARE (2)

ORDNANCE

SAFETY

SWITCH

PLUG

IGNITER

RECEPTACLE

AFT RETAINING
SLOT-

LOCK RING
ASSEMBLY (2)

PLUG & CABLE
ASSEMBLY —<

ANTENNA (4)

FWD LUG

WING (4)—
FWD RETAINING

CANARD (4)

F4-34-1-4 7 2

AFT

INDIVIDUAL MISSILE DRAG

WEIGHT.

LENGTH.

DIAMETER .

WING SPAN.

CANARD SPAN.

LAUNCH AIRSPEED (MAX.).
FLIGHT LIMITS.

1.1

580 POUNDS
11 FEET. 5 INCHES
12.0 INCHES
3 FEET, 2 INCHES
19.0 INCHES
.95 MACH

REFER TO T.O. 1F-4C-1A

Figure 1-100

AGM-12B, -12C, -12E MISSILES

The AGM-12 series weapons are short range, radio
controlled, air-to-ground missiles. Both the AGM-
12B and the AGM-12C missiles are ground burst de¬
vices with either instantaneous or msec-delay fuzing
options. TheAGM-12C, however, is considerably
heavier with a greater explosive yield (figure 1-100
and figure 1-101). The AGM-12E, which is basically
the same as the AGM-12C (figure 1-101), is an air-
burst device. The center section of the AGM-12E
contains over 830 BLU-26/B and BLU-36/B anti¬
personnel bomblets. Shaped charges in the center
section detonate at altitude, rupture the section, and
disperse the BLU bombs over a considerable area.
The following list summarizes the major components
of each missile section assembly. Nearly all com¬
ponents are common to all three missiles.

FORWARD SECTION

Radio Guidance Receiver
Crystal Assembly
Thermal Battery
Pneumatic Control Package

Roll Reference Gyro
Canards

Elec. Plug and Cable Assembly

Fuze Triggering Device

AN/DPN-80 Radar Altimeter (AGM-12E)

Good Guidance Monitor (AGM-12E)

CENTER SECTION

Warhead

Fuze

BLU-26/B and -36/B Pack (AGM-12E)

AFT SECTION
Liquid Engine

Engine Battery (AGM-12C, -12E)

Igniter

Wings

Antenna

Tracking Flares

The following discussion of the above assemblies
pertain to all AGM-12 missiles except where noted
Major differences that exist between missiles are
described at the end of the discussion.

1-210

T.O. 1F-4C-34-1-1

INDIVIDUAL MISSILE DRAG.4.7

WEIGHT. 1789 LBS.

LENGTH.13 FEET 5 INCHES

DIAMETER.17 INCHES

WING SPAN.3 FEET 8 INCHES

CANARD SPAN.24 INCHES

LAUNCH AIRSPEED (MAX).95 MACH

FLIGHT LIMITS.Refer to T.O. 1F-4C-1

FOR AGM- 12E, SUBTRACT 75 LBS
FROM WEIGHT DATA SHOWN HERE.
ALL OTHER DATA IS THE SAME.

IGNITOR
RECEPTACLE

F4-24-1-473

Figure 1-101

FORWARD SECTION
Radio Receiver

The missile receiver, an integral part of the com¬
mand link system, is responsible for the dispersal
of guidance and control signals to missile compo¬
nents. The unit receives the command signal gen¬
erated by the AC, decodes the signal, and directs
the command to the roll reference gyro. The gyro
establishes a vertical reference plane for the ro¬
tating missile and essentially determines which pair
of canards must be deflected for a given command.
Hence, the command signal is directed from the
gyro back to the receiver and on to the pneumatic
control package to complete the command link. The
receiver operates on one of 24 channel frequencies
determined by the crystal plug-in assembly. The
crystal unit, installed through an access door in the
forward section, must match that of the aircraft
transmitter. The receiver contains a deactivation
network that prevents any transient signal from
operating the canards until 0.75 sec. after launch.
After launch, receiver power is supplied by the
missile thermal battery.

Roll Reference Gyro

During flight, the missile is designed to roll at an
angular rate of approximately 500°/sec. at minimum
launch dispersion and provide inflight stability. The
bent tip (AGM-12B) of each wing acts as an aileron
and produces the lift force which causes the counter¬
clockwise rotation (looking from the aft section).
Hence, the gyro is provided to establish a stable,
vertical reference plane within the missile, and
distribute the guidance commands to those canards
which will produce the required response. The
spring-wound gyro is initiated as bomb button volt¬
age melts a fusible link-releasing a lock in the gim-
bal and uncaging the gyro. With the gyro uncaged,
the applied spring force rotates the gyro rotor to
the required operating speed in a fraction of a sec¬
ond. Then the gyro coasts, providing control for a
minimum of 30 seconds.

The decoded command input to the gyro is directed
through brush contacts to four slip rings which are
mounted on the roll gimbal axis. Electrically con¬
nected to the rings are two pairs of commutator seg¬
ments, also mounted on the roll axis shaft. Brush

1-211

T.O. 1F-4C-34-1-1

contacts at the segments pick off the command signal
and apply the signal through relays that actuate the
proper valve in the pneumatic system. The valve
controls a pneumatic piston which physically oper¬
ates the canard pair.

Note that the missile gyro establishes the vertical
reference with respect to the plane of the aircraft at
launch. For example, if the missile is launched with
the aircraft in a left bank and the aircraft is sub¬
sequently rolled level, an up command will result in
an up-left missile response. Thus, the attitude must
be established at missile launch with the wings level.
Considering the missile command link functions dis¬
cussed in other parts of this manual, a time lag of
one-tenth of a second exists between the receipt of
the command signal and the response of the canards.
In one-tenth of a second, the AGM-12B missile will
rotate 50° counterclockwise. Without compensation
for the time lag. the missile would respond in a di¬
rection 50° counterclockwise from the intended com¬
mand i.e., and up command would result in up-left
missile movement. Therefore, the pick-off brushes
in the gyro are biased 50° to compensate for the time
lag. However, the missile will enter flight conditions
where roll rate will deviate from the designed 500°/
sec. and create a situation in which pick-off bias is
no longer sufficient to completely compensate for the
command lag. This is called roll reference shift. A
further discussion of roll reference shift is provided
in the previous part of this manual.

Pneumatic Control Package

The pneumatic control system provides the motor
force that deflects the canards. The package contains
tubular shafts that receive the canards through the
missile skin. A rotational force at the shafts, ap¬
plied through mechanical linkage by pneumatic pres¬
sure, deflects the canards each time a command
signal is applied. The linkage system is spring-
loaded to the neutral position and with each command,
the canards deflect in one direction to full travel.

The pneumatic supply bottle is precharged to 3000 psi
with dry air or nitrogen, and supplies the required
control pressure for a minimum of 30 seconds. At
launch, bomb button voltage energizes a squib-actu¬
ated initiator valve, which releases bottle pressure
to charge the system. The initiator safety pin (figure
1-101) opens the circuit to the squib explosive switch
so that the squib cannot fire during ground oper¬
ations.

Thermal Battery

The missile battery is inert until the AC applies
launch power through the bomb button. This ignites
squibs which dump electrolyte fluid into the battery
plates - activating the battery within 1.5 seconds.
Battery power then energizes a relay in the launcher,
which closes the circuit between the bomb button and
the liquid engine ignitor. The entire missile firing
sequence requires approximately 2.0 seconds. The
AC must hold the bomb button depressed until the
firing sequence is complete and the missile leaves
the launcher. After launch, the battery powers the
missile receiver, the canard solenoid relays, and

the fuze. The battery will maintain the required
power output for a minimum of 30 seconds.

Fuze Triggering Device (AGM-12B and -12C)

The triggering device consists of four linear ele¬
ments (coaxial rods) spaced at 90° intervals around
the inside of the forward section, and one circular
element ai’ound the inside circumference of the sec¬
tion. Each rod element contains an inner electrical
conductor insulated from grounded castings posi¬
tioned at various points along the elements. At
ground impact, the castings are crushed, making
contact with the conductor. This completes the war¬
head circuit and causes detonation. Damage to any
one of the elements will close the fuzing circuit.

Fuze Triggering Device (AGM-12E)

The AN/DPN-80 Radar Altimeter in the nose section
of the AGM-12E initiates the MK-312 fuze. The al¬
timeter operates within a specified range, which in¬
cludes all desirable burst height envelopes for the
BLU-26/B and BLU-36/B dispersion.

Note

The BLU-26/B and -36/B bomblet is dis¬
cussed in this section, part 4. See figure
1 - 86 .

The desired burst height is preset through a dial on
the top right side of the nose section. During mis¬
sile flight, the altimeter system senses the altitude
of the missile, relates this to the preset altitude,
and closes the missile fuzing circuit when the two
match. The fuze trigger signal causes the MK-312
fuze to detonate shaped charges which sever the
center section skin. As the skin panels separate and
move outward into airstream, the nose section is
freed and the bombs are dispersed over the target
area.

Note

Further information covering AGM-12E
flight parameters and fuzing system is con¬
tained in T.O. 1F-4C-34-1-1A, section 4,

CENTER SECTION

Warhead and Fuze (AGM-12B and -12C)

The center section encloses the semi-armor-pierc¬
ing, cartridge-type warhead containing the high ex¬
plosive. The fuze, which is attached to the aft end
of the warhead, is electrically grounded and me¬
chanically safe until launch. Forces applied to the
missile during the acceleration and deceleration
phases of missile flight mechanically arms the fuze
and removes the electrical ground - eliminating the
last safety device in the fuze circuit. Hence, final
fuze arming cannot occur unless engine thrust is
delivered. After launch, a capacitor in the fuze is
charged by the missile battery. At impact, the fuze
triggering device completes the warhead/capacitor
circuit, which discharges the capacitor and initiates

1-212

T.O. 1F-4C-34-1-1

the explosive train. Tumbler switches, which are
energized by the force of impact, are provided to
close the capacitor circuit as a back-up method in
case the fuze triggering device fails. Armament
crews can preset the fuze for an instantaneous
burst, or for a delayed burst (0.008 sec). For tar¬
gets of heavy structure, the delayed fuze will prob¬
ably provide best results.

The center warhead section of the AGM-12E is an
aluminum shell containing a mixed load of over 830
BLU-26/B and -36/B bomblets. Preliminary infor¬
mation regarding bomblet dispersion characteristics
is available in T.O. 1F-4C-34-1-1A.

AFT SECTION

Liquid Engine and Tracking Flares

The liquid engine contains an oxidizer tank and a fuel
tank, each hermetically sealed and mounted in tan¬
dem. A solid propellant gas generator, which is
initiated by the fire signal, provides the pressure
required to break the seals on the propellant tanks.

As the oxidizer and fuel mix, they ignite spontane¬
ously and produce the required thrust. More impor¬
tant to the aircrew, however, is the installation of
the live igniter in the engine section (figures 1-100
and 1-101). The bayonet-type igniter must be in¬
stalled to begin the engine ignition sequence. The
igniter is electrically fired to ignite a booster
charge, which in turn ignites the gas generator men¬
tioned above. Removal of the igniter renders the
engine safe during ground operations and storage.

On the AGM-12B, a red-flagged shorting plug - a
ground safety device - is installed immediately next
to the igniter receptacle to electrically safe the ig¬
nition circuit while the igniter is installed. The tips
of the tracking flares extend into the engine exhaust
area, and are ignited by the hot engine gases. The
flares burn for a minimum of 32 seconds, increasing
in intensity after 9 to 12 seconds burning time.

AGM-12C AND -12E MISSILE

The above discussion points out that the missile rolls
at an average angular rate during flight. The AGM-
12C/E missile wing mounts are designed so that the
plane of the wings is one-half degree from longi¬
tudinal centerline - causing the roll force. The ac¬
tual mean roll rate, and the extent of roll reference
shift, is expected to be about the same as the AGM-
12B.

In the AGM-12C/E missile, there are actually two
power supplies: The forward battery (in the nose
section) supplies voltage to operate the missile sys¬
tems. The engine battery, located directly under the
battery safety plug assembly, supplies voltage to the
engine igniter. Both batteries are activated as the
pilot depresses the bomb button. The safety switch
assemblies are described below.

As far as the aircrew is concerned, the missile fir¬
ing sequence is the same for either missile. Addi¬
tional safety devices are in the AGM-12C/E firing
circuit, however, that must be checked during pre-

(1-212A blank)/ 1-212B

flight operations. These are the battery safety
switch plug and engine safety switch lever shown in
figure 1-101. The battery safety switch plug as¬
sembly is installed during ground operations. When
installed, the unit opens the circuit between the mis¬
sile engine battery and the engine ignitor. (The
bayonet-type ignitor location is also shown in fig¬
ure 1-101.) The battery plug must be removed be¬
fore flight. The engine safety switches, held open by
the lever assembly on the top of the missile, also
locks out the ignitor/battery circuit. The attached
lanyard is hooked onto the armament pylon during
loading operations. As the missile is ejected, ten¬
sion on the lanyard closes the switches and elimi¬
nates the last interlock between the missile battery
and engine ignitor. Hence, engine firing occurs
shortly after ejection.

LASER GUIDED BOMBS (MK 82, 84,
M118)

EQUIPMENT CONFIGURATION

The MK 84 weapon system consist of the MK 84 GP
bomb and the KMU-351/B bomb guidance kit. The
bomb guidance kits and associated attaching hardware
provide a laser, terminal guidance capability for the
MK 84. No specific carriage equipment or weapon
fire control system is necessary; the weapon is
mounted directly on the wing station armament py¬
lons and released through the conventional weapons
controls. No electrical connectors exist between
aircraft and weapon. Hence, weapon monitoring or
controlling functions are not required from the cock¬
pit. Figure 1-102 shows the complete assembly of
KMU-351/B kit components mounted on the MK 84
LDGP bomb.

The M118 system consists of the M118 GP bomb and
the KMU-370/B bomb guidance kit. The guidance
system used with the M118 is essentially the same
as the one used with the MK 84. See figure 1-103.

The MK 82 HS (high speed) components consist of the
MK 82 GP bomb and the KMU-388 bomb guidance kit.
This weapon system performs the same mission
functions as those above, and the guidance unit is
essentially the same (figures 1-102 and 1-103). How¬
ever, the MK-82 system may be carried on MER/
TER shoulder stations, and the MER/TER equipment
is modified to provide specific release sequencing.
(Further information will be supplied when available.)

Note

Ballistics and weapon envelope/profile data
is available for the laser weapons in T.O.
1F-4C-34-1-1A, section VI.

MISSION

The delivery aircraft uses the laser guided bomb in
much the same manner as conventional unguided
bombs in support of air operations including air su¬
periority, interdiction and close air support mis¬
sions. Targets illuminated by a laser are attacked

Change 6

T.O. 1F-4C-34-1-1

using this system. The bomb guidance system, sens- sion may therefore be conducted against targets of
ing the laser energy, derives azimuth and elevation opportunity, or against pre-planned targets of known

steering commands for the movable canards to pro- location. The ballistic tables, for all modes, assume

vide steering to the illuminated target. that the weapon flies an unguided (ballistic) path to¬

ward the target. Thus, the weapon guidance system

Mission planning data is presented for the level,
dive, loft, and dive-toss bombing modes. The mis-

Change 6

1-213

T.O. 1F-4C-34-1-1

1 .

2 .

DRAG INDEX.4.6

WEIGHT. 2052 Pounds

LENGTH. 14 Feet

BOMB DIAMETER.18.0 Inches

FIN SPAN.25.3 Inches

WINGSPAN.45.0 Inches

KMU-351/B:

a. Laser Illumination Detectors

b. Bomb Guidance Computer and Control Section

c. FMU-26B/B Fuze and Forward Fairing Assy
MK-84 Bomb

KMU-351/B Wing Assembly

ATU-35 Drive Assembly (M905 Tail Fuze)

a. Arming Wire to Tail Solenoid

FMU-26B/B or FMU-72/B Battery Initiator Lanyard

Connected to Center Solenoid

6 . Battery Arming Wire

a. Arming Wire Tied to Sway Brace

7. Canards

8 . Thermal Battery Firing Device Safety Pin

Figure 1-102

must accomplish only final course corrections. By
this procedure, the weapon should impact close to
the target if the guidance system malfunctions. Guid¬
ance system acquisition of the target prior to release
is unnecessary. The weapon flies ballistically until
the illuminated target is within the detector field of
view and until the reflected energy is strong enough
to activate the guidance system.

LASER GUIDED BOMB

The MK 84 and M118 bombs are shown in figures
1-102 and 1-103 with their respective guidance kits.

The guidance systems are mounted on the weapon to
become the extreme forward and rear sections. The
major components of the guidance kits are the laser
illumination detector, the bomb guidance control,
and the wing assembly.

LASER ILLUMINATION DETECTOR

This section (figure 1-102) consists of an IR dome,
the optical equipment, an infrared detector, and the
signal mixer and preamplifier networks. The detec¬
tor housing is gimbal-mounted by a universal joint
assembly. During bomb flight, the detector bore-

1-214

Change 5

KMU-370/B:

a. Laser Illumination Detector

b. Bomb Guidance Computer and Control Section

c. FMU-26 B/B Fuze and Forward Fairing Assy
Ml 18 Bomb

KMU-370/B Wing Assembly

ATU-35 Drive Assembly (M-905 Tail Fuze)

a. Arming Wire to Tail Solenoid

FMU-26 B/B Battery Initiator Lanyard,Connected toCenter Solenoid
Battery Arming Wire Tied to Sway Brace

DRAG INDEX.8.2

WEIGHT. 3066 Pounds

LENGTH.13 Feet, 9 Inches

BOMB DIAMETER . . . 24.13 Inches

FIN SPAN. 48.00 Inches

WINGSPAN. 68.00 Inches

4C—34—1— 1 — (105)

Figure 1-103

sight axis is maintained along the bomb velocity
vector by the ring stabilizer. The four-quadrant de¬
tector receives invisible laser energy in the near
infrared spectrum. This in turn generates signals
with characteristics that are a function of the detec¬
tor quadrant or quadrants receiving the energy.

These signals, which eventually become both pitch
and yaw commands, are directed to the guidance
computer.

GUIDANCE COMPUTER

The computer receives the detector signals and per¬
forms the electronic processes which develop the
command signals and operate the guidance control
unit. Some of the computer components include the
log amplifier, comparator logic, and the control
logic circuits. The amplifier video processing cir¬
cuits amplify the weak (long range) video signals and
attenuate the strong (close range) ones in direct pro¬
portion to the strength of the signals. This enables
the continuous detection of both weak and then very
strong signals by the same system. The comparator
network - receiving the output of the amplifier - devel¬
ops the error signals which representthe direction
(left or right, up or down) to be taken to correct
weapon flight. Then the control logic converts these
error signals into solenoid drive signals, which in

turn operate the proper set of steering solenoids.

The control logic also contains circuits which place
the commands in a fin trail status if guidance signals
are lost or if signal inputs are of insufficient
strength.

BOMB GUIDANCE CONTROL

This section of the KMU system consists of the four
movable canards, four solenoids, the thermal bat¬
tery, and a gas generator. These units provide the
drive force which moves the canards in accordance
with the commands generated by the computer. Each
canard pair, which shares a common shaft, is driven
in a bang-bang manner to a total of 5.5° movement in
either direction. In the absence of any command,
the canards are maintained in the trail position by
the airstream.

The thermal battery firing device in the top of the
control unit receives the battery arming wire. The
wire is routed through the forward bomb lug and tied
to the forward rack sway brace. Guidance is always
activated at release. As the weapon separates from
the rack, the arming wire is pulled activating the
thermal battery. Battery voltage is applied to a
3-second delay squib relay; when the relay fires, the
bomb power systems are activated. The 3-second

Change 5

1-215

T.O. 1F-4C-34-1-1

delay allows the bomb and aircraft to separate suffi¬
ciently before any guidance commands can begin.

FORWARD FAIRING ASSEMBLY

The forward fairing assembly provides the mounting
and interfacing structure between KMU guidance kit
and the bomb. The FMU-26 electrical fuze is in¬
stalled through the adapter fairing and into the nose
fuze well of the bomb. This is an electrical fuze
with a self contained thermal battery. A fuze arming
lanyard is routed internally through the bomb, ex¬
tended through a lanyard access between the bomb
lugs, and fized in both the center and forward arm¬
ing solenoids of the MAU-12 rack. At bomb release,

pulling the lanyard initiates battery operation. (FMU-
26 fuzes are further described in this section, Bomb
Fuzes.)

GUIDED BOMB WING ASSEMBLY

The KMU wing assembly provides the necessary lift
for bomb maneuvering flight. Access ports in die
wing fairing provide mounting points for ATU-35
drive assembly, which drives the M-905 bomb tail
fuze. The ATU-35 drive receives a branched arm¬
ing wire which is fixed into the center arming sole¬
noid of the bomb rack. Both the fuze and the drive
unit are described in this section, Bomb Fuzes.

1-216

Change S

T.O. 1F-4C-34-1-1

BOMB FUZES

A fuze is a device used to initiate bomb detonation at
a predetermined time, and under the desired cir¬
cumstances. Since targets are usually selected in
advance of a mission, and the structure of the target
indicates the type of fuzing which would produce the
best results, it is imperative that the correct fuzing
system be installed in the weapon. Additionally,
many weapons can accommodate a large variety of
fuzes which can drastically change the effects. All
tactical fighter pilots must be familiar with the
classification and operation of fuzes to effectively
plan the mode of delivery and insure safe escape
from the contemplated weapon effects. Refer to
Bomb/Fuze compatibility, figure 1-103A

WARNING

• Restricted fuzes and weapons within various
lots are identified and kept current in T.O.
11A-1-1, Ammunition Restricted or Suspended.

• Improper employment of a weapon fuze com¬
bination may result in serious damage to the
aircraft or injury to the aircrew.

Note

For Fuze Safe Arming Times, refer to sec¬
tion IV, and section VI, table of contents.

CLASSIFICATION OF BOMB FUZES

Bomb fuzes may be separated into two general classi¬
fications (refer to figure 1-104):

a. LOCATION. (1) nose fuze, or (2) tail fuze, bomb
fuzes are installed in the nose and/or tail of the
bomb. Nose and tail fuzes usually are not inter¬
changeable because of differences in arming devices
and internal operation. Some fuzes, such as the
FMU-7 series bomb igniter fuze, arm by falling with
either end of the bomb toward the direction of fall
and function at any angle of impact. This type can be
used in either the bomb nose or tail.

b. ACTION. The means of functioning or detonating
the bomb may place the fuze in one of the following
classes:

(1) IMPACT FUZES: Impact fuzes function upon
impact with the target or with a short delay.

In this type, the time delay (if any) is mea¬
sured from the instant of impact, depending
upon the type of explosive train employed:
delay or non-delay.

(2) TIME FUZES: In a time fuze, the delay is
initiated at bomb release from the aircraft -
not at the instant of impact. The time element
is obtained by a mechanical or electrical de¬
vice. An example of this type of fuze is the
M90'7 time fuze.

(3) PROXIMITY FUZES. The proximity fuze is
actually a combination radio broadcasting and
receiving station. The waves, which are con¬
stantly being broadcast by the fuze at a set
frequency, are reflected back from the target
and picked up by the receiving set in the fuze.
When this picked-up impulse is of sufficient
magnitude, an electronic device actuates an
electric detonator. This fuze functions when
it comes in proximity to any target capable

of reflecting its waves. The proximity dis¬
tance can be controlled during manufacture.

An example of this type of fuze is the FMU-
56/B, A/B, B/B.

Fuzes are further classified by the method or arming
and the type of explosive train employed.

METHOD OF ARMING

Fuzes are armed after bomb release, in one (or a
combination) of four methods:

a. VANE. The arming-vane type has a propeller or
anemometer which is rotated after release by air
flowing past the falling bomb. When the vane has ro¬
tated the required number of times, the fuze is
armed. An example of this type of fuze is the M904
nose fuze.

b. PIN. The arming-pin type fuze has a pin or
plunger which is ejected or withdrawn by spring ac¬
tion when the bomb is released. The ejection of the
pin releases the arming mechanism and allows the
fuze to arm, such as the M909 time fuze.

Change 7

1-216A/(1-216B blank)

T.O. 1F-4C-34-1-1

80 MB/TV ll COMP AT 18ILITY

WARNING I

BOMB

IGNI¬

TORS

U-

)UP

35/

Refer to T.O. 11A-1-1, Ammunition
Restricted or Suspended, for current
information reguarding restricted use and
unsafe types or specific lots of ammuni¬
tions, fuzes and air munitions whose
performance or safety for use is question¬
able.

FUZE

BLU-l/B Fire Bomb

BLU-lC/B Fire Bomb

BLU-27/B, A/B Fire Bomb

-o

“O

-a

Q-

□

—I

C-4

MK 82 Snokeye

Q.
O
O
— 1

MK 84 LOGP

M36E2 Incendiary

Q-

“O

-p

CL _
O U.

CO O
'— o

2 :

■

V
n

co”

«✓>

FMU-7A/B, B/B

-o

Ll_

~x>

M23 o< AN-M23A!

•

AN-M47AKMT) Nose

HIli

Wmm,

ATU-35/B, A/B Arming Dr Assy.

□

□1

□

FMU-7/B, A/B, B/B, C/B Elec Nose «. Tail

□

■

WMM,

FMU-26B/B Elec. Nose and Toil

□

□i

111111111

iMl

Illllll

FMU-54/B ond 54A/B Tail

□

WMMk

FMU-56/B, A/B, B/B Proximity Fuze

hiiii

WMM

FMU-72/B Elec Nose and Tail

□

□I

ipll

MK 339 (MT) Nose

Ml and MlAl Fuze Extenders

□

mbs

M152 A1 (MT) Tail

■

M904 El, E2 ond E3 Nose

□

IQ 5

□

□ 5

□I

Mil

M905 Tail

□

WMMi

ill

M907 (MT) Nose

111

|Q 7

liiill

i mm

1 i

111

ipil

■

lull

TAIL FIN CONFIGURATIONS

■■■■■■

■

D fin configuration

11 2 I

Wmm,

NO FINS

|6|6|6

|6l

'' •:

null

III

ill

imm

WMM,

IBS

IHBI

illllll

■

Notes

II All fin configurations are X except F| All stations req uire + (plus) fins, Physically compatible

as noted “ not reliab,e and

_ should not be used.

Aircraft stations 1 and 9 on MER M904 E2 or E3 nose f uze only,

stations 3 and 5 require + (plus) fins.

Aircraft stations 2 and 8 on TER Optional

station 1 require + (plus) fins.

4C-34- 1 — 1—(66)

Figure 1-103A

Change 8

1-217

BOMB FUZE CLASSIFICATION

IMPACT

FUZE EXPLOSIVE TRAIN

D PRIMER

□ DELAY

Q DETONATOR

□ BOOSTER

Q BURSTING CHARGE

Figure 1-104

T.O. 1F-4C-34-1-1

c. INERTIA. The inertia-arming type is armed by
an abrupt change in the velocity of the falling bomb.

d. ELECTRIC. The electrical-arming type fuze is
armed by a battery which is activated at bomb re¬
lease by the extraction of an arming lanyard, such as

| the FMU-7 series fuze used with BLU-l/B fire bomb.

Arming Time Interval

Both arming-pin type and arming-vane type fuzes are
further classified according to arming-time interval-
direct-arming or delayed-arming.

a. DIRECT-ARMING. A direct-arming fuze is
armed immediately when the arming pin is ejected or
when the arming vane has rotated the required num¬
ber of revolutions.

b. DELAYED-ARMING. The delayed-arming fuze
has an arming pin or arming vane which operates as
in the direct-arming fuze, but instead of arming the
fuze directly, the mechanism (controlled by the pin
or vane) initiates a powder train or clockwork mech¬
anism which arms the fuze after a predetermined
time has elapsed, such as the M900 series fuzes.

EXPLOSIVE TRAIN

An explosive train controls the functioning (detona¬
tion) of the bomb (figure 1-104). A train is a se¬
quence of explosions in which a small quantity of
a very sensitive explosive ultimately sets off a large
quantity of a much less sentitive explosive. The two
basic explosive trains are the propelling charge and
the bursting charge as contained in bombs. The type
of explosive used in such large quantities as in the
loading of bombs must be relatively insensitive to
shock and heat. It provides a reasonable degree of
safety in storing, shipping and handling; allows the
bomb to be dropped safe over friendly territory; and
permits the bomb to be used to penetrate a resistant
target such as armor plate, earth, or concrete, be¬
fore exploding. On the other hand, the type of ex¬
plosive used in the fuze must be very sensitive so it
will be sure to explode when impacted by the firing
pin. Such an explosive is not safe to handle except
in minute quantities, and, therefore, is strongly
compressed into a metal capsule called a detonator
which is built into the fuze. The shock generated by
the explosion of a detonator is not sufficiently strong
to be reliable as a means of exploding the large
amount of insensitive explosive which makes up the
main charge of the bomb; therefore, a small quantity
of explosive, which is more sensitive than the main
charge, is placed next to the detonator; this element
is called the booster. The booster is sensitive
enough to be exploded by the detonator and large
enough so that the shock of its explosion will explode
the bursting charge (or main charge) of the bomb.
Such an arrangement of elements is called the ex¬
plosive train, and is the basic method of operation
in all explosive ammunition.

Types of Explosive Trains

The explosive train operation, in both nose and tail
fuzes, may be instantaneous or delayed action.

a. Instantaneous operation begins immediately
upon weapon impact with the target when the firing

pin is driven into the detonator (approximately the
size of an aspirin tablet). The blast from the det¬
onator explodes the booster (about the size of a
flashlight battery) which relays and amplifies the
blast, causing the bursting charge to explode.

b. A delayed action train may be necessary to
allow bomb penetration of a target or to permit the
low altitude delivery aircraft to escape from the
target area. This action requires two additional
components - a primer and a delayed element -
which are placed ahead of the detonator, booster,
and main charge. In this arrangement, the action
begins as a detonation but is converted into a de¬
laying flame by the delay element. The detonator
again changes it into a detonation which continues
through the booster and into the bursting charge.

SAFETY FEATURES

For safety reasons, a bomb must be incapable of
exploding through premature or accidental fuze
action, before it is clear of the aircraft. By defini¬
tion, a fuze is armed when the next normally ex¬
pected event will initiate a function of the fuze. As
previously discussed, that event may be impact, time
train running to completion, nearness to the target,
or water pressure. As shipped, fuzes are in a safe
(unarmed) condition. They are so constructed that
while unarmed they cannot function. To prevent pre¬
mature or accidental functioning of a fuze, a safety
feature is incorporated when it is manufactured. The
most common safety feature in fuzes includes detona¬
tor-safe, arming-stem-safe, and safety-block-safe
devices.

a. A detonator-safe arrangement in a fuze holds one
of the explosive train elements out of alignment with
the other elements. For example, the detonator may
be held out of line with the firing pin until the fuze is
armed.

b. A safety feature commonly found in tail fuzes is
an arming stem which is crewed into the firing pin
plunger. In this type of fuze, the detonator is located
immediately beneath the firing pin. Arming of the
fuze withdraws the arming stem from the firing pin
plunger, thus freeing the plunger. An anti-creep
spring prevents premature movement of the plunger.

c. The safety-block safe feature, commonly found
in nose fuzes, consists of a ring of small steel
blocks which are located between the striker and the
fuze body, thus preventing the firing pin from con¬
tacting the primer or detonator. The arming vane
drives a gear train which, after a definite interval,
permits the safety blocks to be ejected.

ARMING WIRE/LANYARD ROUTING

The authorized arming wire/lanyard routing is pre¬
sented in the Conventional Munitions Loading Pro¬
cedures T.O. 1F-4C-33-1-2. The equipment used to
initiate fuze arming and weapon operation varies
with the weapon and mission requirement. Figure
1-105 shows the arming wire, arming lanyard, and
fin release lanyard routing that provides the air¬
craft commander with the option to release the MK82
Snakeye or M117R bombs either high drag or low
drag.

Change 5

1-219

T.O. 1F-4C-34-1-1

Note

After T.O. 1F-4-805, the arm nose tail switch
positions are SAFE, NOSE, TAIL, and NOSE
and TAIL.

The arm nose tail switch on the multiple weapons
control panel controls voltage application to the se¬
lected solenoid(s) in the bomb rack. The switch
therefore determines which of the bomb fuze arming
wires are released with the weapon or retained by
the solenoid. When a bomb is released ARMED, the
arming wire swivel loops are retained by the arming

solenoids. As the bomb is ejected from the bomb
rack, the arming wires are pulled from the fuzes,
through the swivel loops, and remain attached to the
bomb lugs. The fuzes are then free to become armed
or to operate. If the NOSE option is selected, the
nose fuze functions as described and the tail arming
solenoid releases the swivel loop; the tail fuze arm¬
ing wire and the swivel loop remain with the bomb.

If the bomb is released SAFE, both arming wire
swivel loops are released from the arming solenoids,
the arming wires remain in the fuze safety devices
and the fuzes cannot function. Without fuze opera¬
tion, the bomb is expected to dud.

1-220

Change 4

ARMING WIRE ROUTING
TOR HIGH LOW DRAG INFLIGHT OPTION

M904 NOSE FUZE

FIN RELEASE
LANYARD TIED
TO FIN

SWIVEL AND LINK
TO TAIL

FMU-54
FUZE

SWIVEL AND LOOP
TO NOSE

AFT BOMB LUG

"All data on pages 1-221 thru 1-222, including figure 1-106 deleted.”

Change 5

1-223

T.O. 1F-4C-34-1-1

Figure 1-107

NOSE FUZES

MK 339 MOD 0 MECHANICAL TIME NOSE FUZE

| Refer to MK 20 Mod 2 and Mod 3 cluster bomb this
section.

M904E1 /E2/E3 NOSE FUZE

The M904 (figure 1-107) is a mechanical impact nose
fuze commonly used with general purpose bombs. It
is approximately 9-1/3 inches long and 2 inches in
diameter at the fuze threads. The desired arming
time is set on a calibrated dial. The selective delay
times for M904E1 are: 4, 6, 8, 12, 16and 20 sec¬
onds. The M904E2/E3 has the following delay times:
2, 4, 6, 8, 12, 16 and 18 seconds. The fuze employs
an arming vane to effect arming. The arming time
is independent of release airspeed and is accom¬
plished by the arming vane, a mechanical governor,

and a constant-speed rotating gear train. Impact
functioning (detonation) delay times are provided by
inserting a delay element (M9) in the cavity just
beyond the firing pin. The delay elements are avail¬
able in the following delay increments for both M904
fuzes: instantaneous, 0.01, 0.025, 0.05, 0.10 and
0.25 second.

The fuze has one preflight warning window located in
the fuze body. The other window, above the booster,
is not visible to the aircrew.

WARNING

If the window in the fuze body shows fully red,
the fuze is unsafe and should not be touched.
Call explosive ordnance disposal (EOD) per¬
sonnel immediately. See figure 1-107.

1-224

Change 7

T.O. 1F-4C-34-1-1

Fuze arming begins when the bomb is released from
the aircraft. The arming wire is withdrawn from the
vane and the vane spins in the airstream (operating
range is 150 to 600 knots). After the selected arming
time has expired, the fuze arms.

The M904E1 fuze has a manufacturing arm¬
ing time tolerance of ± 20 percent; the
M904E2 tolerance is ± 10 percent. The nega¬
tive tolerance of the fuze must be used when
determining the minimum arming separation
between weapon and aircraft. The positive
tolerance must be used to determine the mini¬
mum release altitude to insure arming before
impact.

AN-M147A1 MECHANICAL TIME FUZE

The AN-M147A1 mechanical time fuze (figure 1-107A)
is a combination vane and pin arming fuze. This fuze
is used to detonate (or open) the M129E1, E2 leaflet
bomb at a preselected time after the bomb is released
from the bomb rack. When the arming wire is ex¬
tracted from the arming vane and through a hole in
the arming pin, the arming vane ispermittedto be ro¬
tated by the airstream and the arming pin is forced out of
the fuze by a spring. The arming pin was seated in
a notch or a circular timing disk to prevent the alarm
clock-type mechanism from operating. When the
arming pin is ejected, the clockwork turns the disk
at a uniform rate until the timing disk lever drops
into the notch and releases the firing lever and firing
pin. The time is set by rotating the head of the fuze
to locate the timing disk lever at such a distance from
the arming pin as will give the time desired. A
thumbscrew is provided to lock the head in position

AN-M147A1 FUZE

4C—34—1 — 1 —(109)

Figure 1-107A

after the setting is made. The time settings are en¬
graved around the base of the head. Upon completion
of the preset time interval, a small detonator charge
is moved into position under the firing pin. The firing
pin is propelled by a spring in the detonator. The
detonator in turn detonates the booster lead which
detonates the explosive cord to separate the two
halves of the bomb body.

M907 MECHANICAL TIME FUZE

The M907 (figure 1-108) is a mechanical time nose
or tail fuze commonly used for sir burst functioning
of bomb clusters and leaflets bombs. The desired
function time is set on a calibrated dial on the fuze
body. The dial may be set at 1/2 second intervals
between 4 and 92 seconds. There is an airburst
functioning accuracy of plus or minus 1 second. The
fuze employs a four-bladed arming vane to effect
arming. The arming time is independent of release
airspeed and is accomplished by the arming vane, a
mechanical governor and a constant speed rotating
gear train. Arming time is automatically determined
as one-half the preset time on the calibrated dial
when the function time is greater than 10 seconds.
For function times of 4 to 10 seconds, arming will
occur before functioning but not less than one-half
the set time. Delivery airspeeds encompass the
range of 100 to 600 knots TAS. Safety features in¬
clude a slider detonator block containing the detona¬
tor, which is locked out of line with the rest of the
explosive train until arming is completed, and two
arming (warning) indicators. One arming indicator
is an aluminum foil disc located in the lower part of
the fuze body. If the pin is extended through the
window, the fuze is armed.

WARNING

An armed fuze can be determined by check¬
ing the aluminum arming indicator. If the
slider has punctured the aluminum foil disc,
the fuze is armed. Do not touch the fuze and
call explosive ordnance disposal (EOD) per¬
sonnel immediately.

Arming of the fuze starts when the bomb is released
from the aircraft and the arming wire is withdrawn
from the fuze. This permits an arming pin to be
ejected and a movement assembly to begin operation.
Rotational energy for air arming is provided by the
arming vane which drives a constant-speed centrifu¬
gal governor. At the end of the arming cycle, a
spring-loaded slider is allowed to move and bring the
primer into line with the firing pin and booster. A
spring-loaded detent retains the slider in the ARM
position. The fuze is now armed.

Operation of the fuze starts upon release of the
weapon as the arming pin is ejected. This action re¬
moves a projection from the slot in the disc assem¬
bly allowing the clockwork movement to start. Start¬
ing is assured by a spring-loaded starter which

Change 5 1-225

3.5 INCHES

LOCK

SCREW

M72—
PRIMER

F4- 34-1-478

T.O. 1F-4C-34-1-1

ARMING -
VANE (T5)
(4 BLADE)

SETTING

INDEX

ARMING-
WIRE
GUIDE (2)

ARMING-
WIRE

BRACKET

5.0 INCHES

WARNING

WINDOW

(FOR LOAD
CREW USE)

(FOR AIRCREW USE)

BOOSTER

ASSEMBLY

2.5 INCHES DIA

Figure 1-108

1-226 Chonge 1

M.T. M907 (T730)

BLACK POWDER
BOOSTER

M907 BOOSTER ASSEMBLY

T.O. 1F-4C-34-1-1

sweeps across the escape wheel, imparting motion
to it. A timing disc lever rides the periphery of the
disc assembly until the slot in the disc from which
the arming pin was ejected indexes with the lever.
The spring-loaded lever drops into the slot, releas¬
ing the system of levers which in turn releases a
spring-loaded firing pin spring retainer. This re¬
tainer then drives the firing pin into the primer, fir¬
ing the fuze. If impact occurs before the set time
has expired, the firing pin is driven in, shearing the
trigger mechanism and firing the primer.

FMU-26B/B FUZE

The FMU-26B/B fuze (figure 1-111) is an electric
fuze powered by an internal thermal battery. The
fuze can be used as a nose or tail fuze and will pro¬
vide an airburst or impact initiated burst. The air-
burst mode is intended for use only with dispenser
type munitions. The fuze is cylindrically shaped,
approximately 3 inches in diameter and 6.5 inches in
length, and is compatible with bombs that have in¬
ternal plumbing (required to route the arming lan¬
yard) and the standard 3-inch fuze wells (nose and
tail).

The arming lanyard is routed from the charging well
of the bomb through the internal plumbing of the
bomb to a battery firing device which is attached to
the fuze in the nose or tail fuze well. The arming
wire routing can be conducted in one of two ways. In
one method, the free end of the arming lanyard,
which is protruding from the charging well, is routed
through a swivel loop and then into a lanyard lock
which is installed in the charging well and secured
by a lanyard lock nut. When the bomb is loaded on
the bomb rack, the swivel loop is installed in the
bomb rack arming solenoid. In the second method,
the free end of the arming lanyard, is routed through
a firing lanyard adjuster. The excess lanyard is then

cut off. When the bomb is loaded on the bomb rack,
the pull ring of the lanyard adjuster is installed in the
bomb rack arming solenoid.

When a bomb is released armed, the arming solenoid
holds the swivel loop which remains with the bomb
rack as the arming lanyard is withdrawn through the
swivel loop. The arming lanyard remains attached
to the bomb by the lanyard lock. This action cocks
and releases the firing pin which initiates the ther¬
mal battery in the fuze.

When a bomb is released armed, the arming solenoid
holds the pull ring, thus pulling the lanyard. This
cocks and releases the firing pin which initiates the
thermal battery in the fuze. Then a shear pin breaks,
separating the lanyard adjuster from its pull ring.

The pull ring remains with the solenoid; the lanyard
remains attached to the fuze battery firing device.

The activated thermal battery provides the electrical
power for fuze operation. The fuze timing circuitry
provides an arming signal at the pre-set arming
time. This arming signal is used to arm the fuze;
that is, to rotate the detonator from the out-of-line
position to the in-line or firing position. The fuze
timing circuitry then provides the firing (final event)
signal at the pre-set time for impact or airburst
function. The fuze modes with available arming
times and final event times are tabulated below as
follows:

Note

• The arming time tolerance for the short de¬
lay mode is ± 0.300 seconds. With this mode,
the minimum allowable bomb time of flight
(to prevent duds) will be the arming delay
setting plus 0.300 seconds.

• The fuze contains a safing device which duds
the fuze if impact occurs prior to arming.

Change 8

1-227

T.O. 1F-4C-34-1-1

MODE

ARMING TIME

FINAL EVENT

TIME

EVENT

TOLERANCE

Airburst 1

Selectable

1.9 to 99.9 sec in

0.5 sec increments

Selectable

Occurs 0.1 sec after
arming

± 0.3 sec

Impact 2

Short Delay

Selectable

2.0 to 20.0 sec in

2.0 sec increments

Selectable

Non-delay, 0.010

0.020, 0.050, 0.100,
or 0.250 sec

± 10% or ± 0.002
sec, whichever
is greater

The event and arm times are set into the fuze with an
alien wrench and are displayed in the windows on the
face of the fuze. The safe pin locks the fuze rotor in
the out-of-line position until after the fuze is in¬
stalled in the bomb. Prior to departure of the loaded
aircraft from the loading area, the safe pin is re¬
moved from the fuze and replaced with the seal pin.
The seal pin prevents entry of moisture into the fuze.

The aft end of the fuze (the booster end) has a pie-
shaped section to accept a booster. Two kinds of
boosters are used: a 45-gram RDX booster which is
secured to the fuze by tape, and a 5-gram M-5 pro¬
pellant booster (FZU-l/B booster) which is secured
to the fuze by a metal bracket. The bracket is also
used to activate the airburst mode. The aft end of
the fuze also has a safe plug and a safety switch.

The safe plug is in the fuze only during shipping and
handling, and is removed prior to installation of the
fuze into the bomb. The battery firing device is in¬
stalled in the cavity vacated by the safe plug.

When the fuze is used with dispensers, the FZU-l/B
(airburst) booster is used. The lanyard lock, and the
45-gram RDX booster are not used in dispensers.
When the fuze is used in high explosive bombs, the
45-gram RDX booster (booster and tape assembly) is
used.

The fuze safety switch has three positions: RED,
GREEN (normal), and BLUE (airburst). The GREEN
(normal) position keeps the firing circuit to the deto¬
nator disabled for approximately 6.6 seconds after
bomb release. The safety switch should be kept in
the GREEN position for all medium delay (skip mode)
settings. It should also be kept in the GREEN posi¬
tion for all short delay (dive mode) settings, except
when operational delivery conditions are such that the
time from bomb release to impact will be less than
6.6 seconds. For releases where this time is less than

6.6 seconds, the safety switch must be set in the
RED position to assure fuze function at the pre-set
time. The BLUE position can be selected only when
the FZU-l/B (airburst) booster is installed. The
FZU-l/B booster has a metal bracket which holds
the spring-loaded safety switch in the BLUE position.
When the FZU-l/B booster and bracket are removed,
the safety switch will spring to the GREEN position.
The airburst mode is inoperative when the safety
switch is not in the BLUE position. If the fuze selec¬
tor switch is set in the airburst mode, but the safety
switch is not set in the BLUE position, the fuze will
not detonate airburst, but will detonate at impact
through the airburst back up circuit.

Whether the fuze is set in the RED or GREEN
position, the minimum release altitude, or
vertical drop required for safe escape, must
be carefully observed as specified in the ap¬
propriate minimum release altitude/fuze
arming time tables.

The fuze can be used more advantageously in the
nose fuze well. Nose installation permits easier ac¬
cess for inspection by the aircrew and for changes of
arming and event time settings if such changes are
required after initial loading. The inspection and
changes can be done if the nose plug is removed. If
the tail fuze well is used, the initial fuze settings
are most easily accomplished before the fuze is in¬
stalled in the bomb. After fuze installation, settings
are most easily accomplished with the bomb tail fin
removed. Changes in tail fuze settings require re¬
moval of the fuze from the bomb, or removal of the
tail fin and fuze nose plug.

"AH data on pages 1-229 thru 1-231
including figures 1-109 thru 1-110 and
1-112 deleted."

1-228

Change 8

T.O. 1F-4C-34-1-1

BLUE SAFETY SWITCH

FZU-1 B (AIRBURST)
BOOSTER HOLDER

AIRBURST BRACKET
HOLDS BLUE SAFETY SWITCH
IN BLUE (AIRBURST) POSITION

FZU-l/B (AIRBURST)
BOOSTER

(SAFING PLUG
REMOVED)

SAFING PLUG

EVENT/ARM SELECTOR

SAFING SWITCH
SPRING LOADED
TO GROUND BURST
POSITION

(BOOSTER IS REMOVED)

SfCONDS

AIRBURST (BLUE AREA)

(SHORT ARM DELAY
GROUND BURST
(RED AREA)

NORM (GREEN AREA)
6.6 SEC ARM DELAY
(GROUND BURST)

Figure 1-110

"All data on page 1-230 deleted."

Change 4

1-229/(1-230 blank)

UNCLASS WED

T.O. 1F-4C-34-1-1

FMU-26B/B FUZE

F4-34-1-427

Figure 1-111

T.O. 1F-4C-34-1-1

FMU-30/B NOSE FUZE

The FMU-30/B fuze and power supply (figure 1-112)
is a pressure-sensitive fuze. It is intended pri¬
marily for use in the standard 3 -inch diameter fuze
well of the BLU-31/B land mine. The fuze contains
a battery power supply, an electronic assembly com¬
posed of electromagnetic timers and sequential logic
circuitry, an electromechanical arm/safe mech¬
anism, a rotor-mounted detonator with an out-of¬
line position, and a pressure detection system con¬
sisting of an amplifier and three piezo-electric sen¬
sors mounted under sensor covers in the sides of
the nose forging. An externally mounted booster, at¬
tached as shown in figure 1-112, is used with the
fuze to enable it to initiate the high explosive in the
land mine. Figure 1-112 also indicates the location
of the target selector adjustment plug and the sensi¬
tivity adjustment. All FMU-30/B fuzes are shipped
with the target selector in the No. 1 position. If any
other position is required, the pipe plug must be re¬
moved and the desired position selected. For addi¬
tional information on the operation of the FMU-30/B
fuze, refer to the secret supplement to this delivery
manual, T.O. 1F-4C-34-1-1B.

WARNING

If the color visible through the arm/safe in¬
dicator window on the side of the nose forg¬
ing (see figure 1-112) is GREEN, the FMU-
30/B fuze is safe. If the RED color is visible
the rotor may have become unlocked and the
fuze must be considered armed. In this event
the fuze must not be used. Do not touch fuze
and notify explosive ordnance disposal (EOD)
personnel immediately.

FMU-72/B LONG DELAY FUZE

The FMU-72/B long delay bomb fuze is cylindrically
shaped, approximately 3 inches in diameter, and
6 l/2 inches long. The fuze and components (figure
1-113) are used with compatible munitions to assem¬
ble a completely fuzed munition.

The FMU-72/B fuze is compatible with the nose and/
or tail fuze wells of all bombs with internal plumbing
and the standard 3-inch fuze well, which include the:

a. M117, 750-lb., GP Bomb

b. Ml 18, 3000-lb., GP Bomb

c. Mk 82, 500-lb., GP Bomb

d. Mk 83, 1000-lb., GP Bomb

e. Mk 84, 1500-lb., GP Bomb

The FMU-72/B can be used either in the nose or tail
fuze well. Settings must be made prior to installing
the fuze in the fuze well. If a change in a setting is
required after installing the fuze, it must be re¬
moved from the bomb to make the change.

I CAUTION

Since the fuze settings are not visible to the
pilot for inspection, the munitions handling
and loading personnel must be carefully
briefed on required settings.

The FMU-72/B fuze is activated upon armed release.
The swivel and link assembly is held by the arming
solenoid and stays with the aircraft; when the bomb
is released, the lanyard is pulled. This pull (greater
than 36 pounds) cocks and releases the firing pin
which initiates the liquid ammonia battery in the fuze.
The battery provides electrical power for fuze op¬
eration. The arming circuitry provides a fixed delay
for the signal for arming. The arming signal is used
to arm the fuze, that is, rotate the detonator from
the out-of-line position to the in-line or firing posi¬
tion. To assure that the detonator does not fire at
arming, it is grounded until impact occurs, and the
power source which fires the detonator is not charged
until 33 seconds after impact. The fuze timing and
counting circuitry provide the firing or final event
signal at the set event time after impact. The arming
time and selectable event times are listed below:

a. Arming Time: Fixed at 6.0 (+1.5, -1.0) seconds

b. Event Times: Selectable in 20-minute incre¬
ments from 20 minutes to 5 hours; 1-hour increments
from 5 hours to 16 hours; 2-hour increments from

16 hours to 30 hours; and 3-hour increments from 30
hours to 36 hours.

WARNING

When the FMU-72/B fuze is used in general
purpose bombs, select minimum release al¬
titudes which will provide safe escape from
bomb fragments for instantaneous or contact
bursts. This is required to protect the air¬
craft and aircrew in the event of a premature
bomb detonation at initial impact. To pre¬
clude ricochet, release conditions for general
purpose bombs should provide a trajectory
angle at impact in excess of 40°.

For detailed information concerning anti-disturbance
feature and impact spacing, refer to T.O. 1F-4C-34-
1-1A.

The fuze contains a safing switch which duds the fuze
in the event impact occurs prior to arming.

Note

To assure adequate time for the FMU-72/B
fuze to arm prior to impact, use the mini¬
mum release altitudes as specified in the
fuze arming time tables for the M904E2/

M905 fuze with a 6 second arming delay set¬
ting, section VI.

1-232

Change 5

T.O. 1F-4C-34-1-1

FMU-72/B LONG DELAY FUZE

The FMU-72/B long delay bomb fuze is cylindrically
shaped, approximately 3 inches in diameter, and
6 1/2 inches long. The fuze and components (figure
1-113) are used with compatible munitions to assem¬
ble a completely fuzed munition.

The FMU-72/B fuze is compatible with the nose and/
or tail fuze wells of all bombs with internal plumbing
and the standard 3-inch fuze well, which include the:

a. M117, 750-lb., GP Bomb

b. M118, 3000-lb., GP Bomb

c. Mk 82. 500-lb., GP Bomb

d. Mk 83, 1000-lb., GP Bomb

e. Mk 84, 2000-lb., GP Bomb

Since the fuze settings are not visible to the
pilot for inspection, the munitions handling
and loading personnel must be carefully
briefed on required settings.

arming, it is grounded until impact occurs, and the
power source which fires the detonator is not charged
until 33 seconds after impact. The fuze timing and
counting circuitry provide the firing or final event
signal at the set event time after impact. The arming
time and selectable event times are listed below:

a. Arming Time: Fixed at 6.0 (+1.5, -1.0) seconds

b. Event Times: Selectable in 20-minute incre¬
ments from 20 minutes to 5 hours; 1-hour increments
from 5 hours to 16 hours; 2-hour increments from

16 hours to 30 hours; and 3-hour increments from 30
hours to 36 hours.

WARNING

For detailed information concerning anti-disturbance
feature and impact spacing, refer to T.O. 1F-4C-34-
1 - 1 - 1 .

The fuze contains a safing switch which duds the fuze
in the event impact occurs prior to arming.

Note

To assure adequate time for the FMU-72/B
fuze to arm prior to impact, use the mini¬
mum release altitudes as specified in the
fuze arming time tables for the M904E2/

M905 fuze with a 6 second arming delay set¬
ting, section VI.

(1-231 blank)/l-232

Change 8

/tell

i r :

i' I

SJS

ill

T.O. 1F-4C-34-1-1

FMU-72/B LONG DELAY FUZE

BOOSTER

BOOSTER END VIEW

Figure

FMU-81/B SHORT DELAY FUZE

The FMU-81/B short delay bomb fuze is cylindrically
shaped, approximately 3 inches in diameter, and 11
inches long. The fuze and components (figure 1-113A)
are used with compatible munitions to assemble a
completely fuzed munition. The FMU-81/B fuze is
compatible with the nose and/or tail fuze wells of all
low drag bombs with internal plumbing and the stan¬
dard 3-inch fuze well, which include the:

a. M117, 750-lb, GP Bomb

b. M118, 3000-lb, GP Bomb

c. Mk-82, 500-lb, GP Bomb

d. Mk-83, 1000-lb, GP Bomb

e. Mk-84, 2000-lb, GP Bomb

f. BLU-31/B, 750-lb, Demolition Bomb

4C-34-1-1-0 15)

1-113

The FMU-81/B fuze is also intended for use with
guided bombs.

The FMU-81/B consists of three major assemblies:
fuze, FZU-2/B fuze booster, firing lanyard adjuster
(MAU-162/A) and lanyard assembly. An auxiliary
booster clip is provided as an accessory for guided-
bomb applications. The fuze consists of a body,nose,
safety clip, thrust washer, booster clip, battery
firing device (BFD), lanyard assembly, hitch pin with
warning tag, and safe pin. The body is a steel cylin¬
der with a window near the end opposite the nose.
Contained within the body are a battery, a safing and
arming mechanism (S&A), and an electronics as¬
sembly. The nose is a cone-shaped casting 4.2 inches
in diameter, integral with the fuze body. It contains
two thumbwheel setting knobs, one for arming delay

1-234

Change 5

T.O. 1F-4C-34-1-1

and one for impact delay, held in place by a fuze nose
plug and connected to selector switches in the elec¬
tronics assembly by two mating shafts. A seal plug
and safety clip with warning tag complete the unit.

The thrust washer is a spacer surrounding the fuze
body at the base of the nose and has an outer diam¬
eter of 4.35 inches. The thrust washer is used only
when the fuze is installed in the nose fuze well. The
booster clip is a spring-steel holder that fits into the
booster recess at the end of the fuze body. The BFD
is a steel cylinder integral with the fuze body that
protrudes from the recessed end of the body. It con¬
tains a firing pin held in restraint by a shear wire
until initiated by a pull from the lanyard. The lan¬
yard assembly is a braided steel cable connected to
the BFD by a ball and shank. The hitch pinis a safety
pin inserted in a hole in the BFD housing and lanyard
rod. This pin is removed before fuzing the bomb.

The safe pin is a slender steel rod that is visible
through the window in the fuze body and extends
through the body and nose to the seal plug.

The fuze booster is shaped to fit the contour of the
fuze booster cavity and to be snapped into position
under the booster clip.

The firing lanyard adjuster (MAU-162/A) consists of
a lanyard tie-off block, a pull ring, and a shear wire.

The auxiliary booster clip is a spring-steel holder
that holds three supplementary boosters in place
around the BFD when the fuze is used in a guided
bomb.

Safety Features

A SAFE position of the arming-delay-setting thumb¬
wheel renders the arming circuit inoperable in this
position. Locking plates behind the arming-delay and
impact-delay setting thumbwheels prevent accidental
movement of the thumbwheels during ground handling
of the fuze. A safe pin reveals a potentially armed
condition of the fuze by visibly protruding through a
seal plug on the fuze nose. The safe pin holds .the
rotor out of line until the pin is driven through the
plug by the arm-enable bellows.

WARNING

If the safe pin is protruding through the seal
plug in the fuze nose, the fuze shall be con¬
sidered armed. In this event, the fuze shall
not be used. Do not touch fuze and notify ex¬
plosive ordnance disposal (EOD) personnel
immediately.

A safety clip on the fuze nose prevents the safe pin
from releasing the rotor until the safety clip is man¬
ually removed during installation in a bomb. If the
BFD is accidentally initiated during handling, the
safe pin permanently locks the safety clip in place to
reveal a defective fuze condition to the munition han¬
dler. A hitch pin prevents actuation of the BFD until
manually removed during bomb installation.

The S&A provides out-of-line safety until the rotor
is freed by movement of the safe pin and propelled
in line by an arming bellows after BFD initiation. If
an impact of greater than 250 G should occur prior to
arming, the safing switch and/or the detonator enable
switch will function and prevent the fuze from arming.
If an arming signal should be generated prior to arm-
enable (removal of the safe pin), the rotor will at¬
tempt to rotate and will deform a locking tang, which
then permanently locks the rotor out of line. The S&A
also prevents battery voltage from reaching the event
circuitry before mechanical arming occurs.

The arm-enable circuitry prevents premature actua¬
tion of the arm-enable bellows by means of a resis¬
tor-capacitor combination that limits the enable-
bellows charging current until the pre-set timing
circuit releases a voltage pulse and triggers the
capacitor to discharge into the bellows.

FMU-81/B FUNCTIONAL DESCRIPTION

Arming Delay

Any of nine arming-delay settings (4, 5, 6, 7, 8, 10,
12, 14, or 20 seconds) or a SAFE setting can be
selected by means of the thumbwheel setting knob
(figure 1-113A) of the arming-delay selector switch.
The tolerance on the arming delay is ± 5%. The arm¬
ing-delay settings may be made before or after in¬
stallation of the fuze in the bomb.

Impact Delay

Any of six impact-delay settings (.00, .01, .02, .05,
.10, or .25 second) can be selected by means of the
thumbwheel setting knob (figure 1-113A) of the im¬
pact-delay selector switch. The impact-delay set¬
tings may be made before or after installation of the
fuze in the bomb.

The fuze can be used more advantageously in the nose
fuze well. Nose installation permits inspection by
the aircrew and for changes of arming and event time
settings if such changes are required after initial
loading. If the tail fuze well is used, the removal of
the safe and arm safety clip cannot be verified by ex¬
ternal inspection of the bomb, and the removal of the
safety clip immediately prior to launch requires the
removal and reinstallation of the tail fin access cover.
Also when returning to base with unexpended or hung
bombs, timely verification of the armed/unarmed
status of the tail fuze cannot be ascertained by ex¬
ternal inspection of the bomb.

Operational Sequence

Upon bomb release, a lanyard pull of 20 pounds or
more shears a pin in the BFD and releases the BFD
firing pin. The firing pin initiates a primer cap,
which in turn initiates heat paper within the battery.
The heat paper raises the battery temperature to
generate battery voltage. After a battery rise time
of 0.4 ± 0.125 second, the battery produces the 11
volts necessary to operate the timing and control
circuitry in the fuze. At approximately 3/4 of the
set arm time, the enable bellows motor is activated,

Change 5

1-234A

(IMPACT)

DELAY-SETTING

THUMBWHEEL

PUNCTURED

THUMBWHEEL

POTENTIALLY
ARMED CONDITION

SEAL PLUG

" ■ . . .*-

mu-81/B SHORT VUAy FUZE \

1-234B Change 5

Figure 1-113A

removing the safe pin block on the S&A. At the set
arm time the arming bellows motor is activated,
moving the detonator to the in-line position. On im¬
pact, the fuze functions after elapse of the pre-set
impact delay.

FMU-56/B PROXIMITY FUZE

The FMU-56/B (figure 1-114) is a self-powered dopp-
ler radar proximity fuze used to open a free-falling
cluster bomb unit (CBU): CBU-24B/B, -29B/B,
-49B/B, and -52A/B series. The fuze has provisions
for presetting fuze arming time and dispenser height
of burst. The fuze is constructed in two cylindrically
shaped sections. The smaller section fits into the
fuze well of the munition and the larger section pro¬
trudes externally.

The FMU-56/B proximity fuze is an altitude sensing
fuze with 9 settings available for burst altitude and
9 safe separation settings (2 to 18 seconds). Burst

settings are set on the fuze prior to installation in
the munition; safe separation settings (arming time)
may be made after the fuze is installed in the muni¬
tion. Switch position and corresponding height of
burst (HOB).

HOB SELECTOR SWITCH

Switch Position

Function (ft AGL)

LOCKING PLATE

4C-34—1—1-(217)

T.O. 1F-4C-34-1-1

The available switch positions and corresponding
safe separation times for the arming time selector
are listed in the following table.

ARMING TIME SELECTOR SWITCH

Switch Position

Arming Tin

S or 0

Safe

A or 1

B or 2

C or 3

D or 4

E or 5

F or 6

G or 7

H or 8

J or 9

Use of a minimum safe separation setting of
3 seconds is recommended for all release
situations to assure adequate aircraft/muni-
tion separation distance at cluster opening
time.

The fuze subassembly contains the doppler ranging
radar, battery, and safing and arming device. The
fuze subassembly is equipped with two safety devices
which are removable; a safing plug which is removed
before loading and a shorting pin which is removed
before flight. Construction consists of a steel cylin¬
der to which a threaded aluminum collar and a plas¬
tic radome are attached. A retainer clip attached to
a depression in the rear of the steel cylinder holds
one booster fuze (FZU-l/B). The threaded collar
secures the fuze assembly in the CBU fuzewell. The
FZU-l/B fuze booster contains five grams of M5
propellant in a metal container topped by a foam
filler. The booster is attached to the rear of the
fuze assembly. Detonation of the booster causes nose
cap of the CBU to separate.

The battery firing device consists of a steel initiator,
a retaining clip and a lanyard of steel cable. The
lanyard is routed through the CBU lanyard tube as
illustrated in figure 1-106. The fuze subassembly is
positioned over the initiator which allows the initia¬
tor firing pin to strike the battery primer when the
lanyard is pulled.

After the CBU is released from the aircraft, the
battery firing device is activated when the lanyard is
pulled. The firing pin of the battery firing device
initiator strikes the battery primer, igniting the
battery which applies power to the fuze circuitry and
starts the arming timer. The arming timer runs for
its preset time, at the end of which the fuze will arm
provided the velocity sensor switch is closed.

When energized, the radar circuitry of the fuze is
continually checking the CBU's height above the
ground and the vertical component of its velocity
with respect to the ground. The height above the
ground is measured by determining the time re¬
quired for the radar pulse to reach the ground and

return to the fuze. The closing velocity of the CBU
is determined from the amount of doppler shift in the
returned signal with respect to the fuze's internal
reference oscillator. When the height above ground
(measured by the fuze) is the same as the height of
burst, and the closing velocity of the munition is
greater than a predetermined minimum value, the
detonator fires through the booster ignition port of
the fuze housing to detonate the booster. Detonation
of the booster pushes the FMU-56/B fuze and the
CBU nose cap out of the CBU cannister allowing the
CBU to separate into two pieces and disperse the
payload.

Safety Features

Before the FMU-56/B will arm, the following se¬
quence of events must occur:

a. The SAFING PLUG must be removed from the
fuze assembly.

b. The battery must be ignited.

c. The SHORTING PIN connected as a short across
the battery must be removed.

d. The ARMING TIMER SWITCH must be set to a
position other than 0.

e. Air flow sensed by the VELOCITY SENSOR ports
at the expiration of safe separation time must ex¬
ceed 150 knots.

When safing plug is installed in the rear of the fuze
subassembly, the safing plug locks the safing and
arming rotor in the SAFE position. With the safing
plug in place the battery cannot be ignited. If the
battery is ignited while the shorting pin is installed
in the proper receptacles, the battery will be shorted
to ground and will discharge. When the arming timer
switch is set to 0, the safe separation timer will not
run and the safing and arming device will not re¬
ceive an ARM signal and will remain in the SAFE po¬
sition. When the velocity of air sensed at the velocity
sensor ports is less than 150 knots, the switch will
remain open, breaking the arm circuit to the safing
and arming device.

Note

Since the fuze height-of-burst and arming
time selector switch positions are set by the
load crew, the munitions handling and load¬
ing personnel must be carefully briefed on
the required settings.

FMU-56A/B PROXIMITY FUZE

The FMU-56A/B is an improved version of the FMU-
56/B (figure 1-114). The major differences between
the FMU-56/B and FMU-56A/B fuzes are in the se¬
lectable safe separation times (SST), the selectable
heights of burst (HOB), and provisions in the FMU-
56A/B for presetting and ECM operational mode.

For additional information concerning the ECM op¬
erational mode, refer to T.O. 1F-4C-34-1-1A. The
FMU-56A/B ECM switch must be set to ON or OFF
as required by the mission.

Change 5

1-235

T.O. 1F-4C-34-1-1

FMU-56/B, A/S, S/B PROXIMITY FUZE

SHORTING

PITOT TUBE
HOUSING

ARMING TIMER
SWITCH

BOOSTER RETENTION CLIP

SHORTING PIN

4C-34-l-l-(m>

Figure 1-114

-236 Change 5

T.O. 1F-4C-34-1-1

The arming time and height of burst values that are
available with the FMU-56A/B fuze are as follows:

Switch

Arming

Switch

Height of

Position

Time-sec

Position

Burst-ft

Safe

250

500

800

1100

1500

1800

2000

2200

2500

3000

Note

The arming timer tolerance for the FMU-
56/B and FMU-56A/B fuzes is ± 10% of the
selected value or ± 0.5 sec, whichever is
greater. During mission planning, where
either FMU-56/B or FMU-56A/B fuzed mu¬
nitions are involved, the munition time of
flight from release to function altitude must
be greater than the arming timer setting plus
the tolerance. This procedure must be care¬
fully observed. If the munition passes
through the selected function height prior to
the expiration of the pre-set arming time,
the fuze will not function and a dud round will
be the result.

In addition to the major differences described above,
all FMU-56A/B selector switches have been located
on the antenna support collar to provide for complete
selectability after the fuze has been installed in the
munition. The velocity (pitot) system has been re¬
designed to provide for improved sealing of the fuze
radome. The two stage safe separation (SST) func¬
tion in the FMU-56A/B will deploy the pop-out pitot
tube through a fracture disk in the nose of the radome
prior to the expiration of the selected safe separation
time (SST). The pop-out pitot tube will then sample
the air stream and the contacts of the velocity switch
will close if the velocity sensor detects an air flow
greater than 150 knots. This switch closure allows
the output of the SST to proceed to the bellows actua¬
tor in the safety and arming device. The function of
the safing plug, safing pin, and the safe position of
the SST selector switch are unchanged.

Safety Features

The following additional safety features are available
with the FMU-56A/B:

a. Impact switch. Should the fuze impact the ground
prior to the expiration of the preset safe arming
time, the impact switch will prevent the fuze from
arming.

b. Visual arm indicator. When the velocity sensor
system is activated, a pitot tube will be extended
from the radome. The extended pitot tube is an indi¬
cation that the battery has been ignited and the fuze
should be treated as armed.

FMU-56B/B PROXIMITY FUZE

The FMU-56B/B proximity fuze is identical to the
FMU-56A/B except the FMU-56B/B has an integral
battery firing device and lanyard and a safing pin in
lieu of a shorting pin. The lanyard, battery firing
device and fuze must be installed in or removed from
the dispenser as a unit.

Note

For ripple releases of FMU-56 fuzed muni¬
tions, if different heights of burst are to be
used the first munition in the ripple release
should be set to the lowest height of burst.

TAIL FUZES

M905 TAIL FUZE

The M905 (figure 1-115) is a mechanical impact tail
fuze commonly used with general purpose bombs. It
is approximately 6-1/8 inches long and 2 inches in
diameter at the fuze threads. Arming is effected by
the ATU-35/B or -35A/B arming drive assembly
through a flexible shaft instead of by an arming vane
(figure 1-115). The arming time is independent of
release airspeed; this is accomplished by the arming
drive assembly, flexible shaft, mechanical governor,
and constant-speed rotating gear train. The desired
arming time is set on a calibrated dial with selective
delay time of 4, 6, 8, 12, 16, and 20 seconds. Im¬
pact functioning (detonation) delay times are provided
by inserting a delay element (M9) in the cavity just
beyond the firing pin. The delay elements are avail¬
able in the following delay increments: Instanta¬
neous, 0.01, 0.025, 0.05, 0.10 and 0.25 second. The
fuze has one warning window visible for aircrew pre¬
flight located in the fuze body. If the fuze should be¬
come armed, the warning window will show fully red.
The other window, above the booster, is not visible
to the aircrew.

WARNING

If the window in the fuze body shows fully red,
the fuze is unsafe and should not be touched.

Call explosive ordnance disposal personnel
(EOD) immediately.

Fuze arming starts when the bomb is released from
the aircraft and the arming wire is withdrawn from
the vane tab of the arming drive assembly. This per¬
mits the vane tab to rotate the inner parts of the fuze
(operating range of the fuze is 150 - 600 knots). After
the selected arming time has expired, the firing pin
is free to move in the direction of flight upon suffi¬
cient deceleration of the fuze. An anti-creep spring
prevents premature movement of the firing pin due
to velocity changes of the bomb during free fall. At
the expiration of the arming time the fuze arms. A
detent locks the rotor in the armed position, and the
fuze is then armed.

Change 5

1-237

T.O. 1F-4C-34-1-1

TAIL FUZES ^

ATU-35/B DRIVE ASSEMBLY

ARMING

WIRE

WARNING

WINDOWS

— DELAY
ELEMENT T2

— TIME SCALE FOR
ARMING DELAY SETTING

ATU-35A/B DRIVE ASSEMBLY

RESTRAINING PIN

SAFETY
COTTER PIN
AND FLAG

Figure 1-115

The M905 fuze has a manufacturing arming
time tolerance of ± 20 percent. The negative
tolerance of the fuze must be used when de¬
termining the minimum arming separation
between weapon and aircraft. The positive
tolerance must be used to determine the
minimum release altitude to insure arming
before impact.

When the bomb impacts on target, the inertia gen¬
erated by the bomb causes the firing pin assembly to
move forward and strikes the primer in the delay
elements, thus initiating the explosive train.

FMU-7 Series Fuzes and Initiators

The fire bombs employ the FMU-7 Series fuzes
(figure 1-116) and the M23 or AN-M23A1 igniters
(figure 1-117) for nose and tail fuzing. The fuze is
electrically armed by an initiator assembly installed

between the bomb suspension lugs. An arming lan¬
yard is connected from the initiator assembly to the
bomb rack solenoid. The initiator assembly consists
of a spring-loaded firing pin, a 1.5 volt thermal bat¬
tery, and electric cabling that connects the initiator
to the fuzes through internal channels in the fire
bomb.

The fuze functions by mechanical impact at any angle
of impact and can be used as either a nose or a tail
fuze. In the fire bomb, the fuze is enclosed in an
M23 or AN-M23A1 igniter, and forms part of the
fuzing network consisting of an arming lanyard and
initiator (figure 1-116) and electric cabling. The
fuze is 2 inches in diameter at the fuze threads and
4.2 inches long. Arming is accomplished by the
initiator through a spring-loaded firing pin and ther¬
mal battery assembly. The fuze functions instanta¬
neously upon impact, and has no provisions for de¬
layed functioning. Safety features are of the arming-
stem safe principle. The FMU-7/B fuze includes a
red-tipped indicator pin permitting visual inspection.
The FMU-7A/B, B/B, C/B includes a seal permit¬
ting visual inspection.

1-238

Change 5

T.O. 1F-4C-34-1-1

Figure 1-116

Change 5

1-239

T.O. 1F-4C-34-1-1

The initiator assembly (figure 1-116) is located on
the top of the fire bomb between the suspension lugs.
It consists of an arming lanyard, spring-loaded firing
pin and 1.5-volt thermal battery. Electric cabling
connects the initiator to the fuzes through internal
channels in the fire bomb.

Arming is initiated as the weapon is ejected from the
aircraft pylon. The arming lanyard (retained by the
pylon arming solenoid) pulls the initiator cap from
the initiator. As a result, a spring-loaded firing pin
is released, forcing it against the primer, and acti¬
vating the thermal battery. The output of the thermal
battery rises to a 1.5 volts pulse. The pulse is passed
through the electrical cabling in the fire bomb to a
bellows motor in the fuze. The bellows motor with¬
draws the arming pin which in turn frees the firing
pin. Hie fuze is now armed. The time from firing
of the thermal battery to completion of fuze arming
is 0.5 to 1.1 seconds for the FMU-7/B fuze and 0.3
to 0.9 second for the FMU-7A/B, B/B, C/B fuzes.
The FMU-7/B fuze when armed, will have a pin
protruding from the center of the fuze head. The
FMU-7A/B, B/B, C/B fuze when armed, will have
a seal broken in the center of the fuze head. Once
armed, the fuze cannot be reset.

WARNING

If pin protrudes through hole in center of
FMU-7/B fuze head or if seal is broken in
center of FMU-7A/B, B/B, C/B fuze head,
fuze is armed. Do not touch the fuze and
notify explosive ordnance disposal (EOD)
personnel immediately.

Upon impact, the fuze firing pin and firing pin holder
are forced together, firing the primer. Functioning
of the fuze causes ignition of the M23 or AN-M23A1
phosphorus igniter which, in turn, ignites the napalm
mixture.

M23 OR AN-M23A1 IGNITER

The M23 or AN-M23A1 igniters (figure 1-117) are
cylindrical in shape and rounded at one end. In the
rounded end is a fuze well.designed to receive the
FMU-7/B, A/B, B/B, C/B bomb fuze. The body of
the igniter is filled with 1.25 pounds of white phos¬
phorus (WP).

When the fuze impacts a target, the fuze functions
and the booster in the fuze detonates, bursting the
igniter and scattering the white phosphorus filling.
The phosphorus ignites spontaneously upon exposure
to the air and ignites the scattered filling of the
bomb.

WARNING

The coarse white phosphorus in the igniter
liquifies at 111°F and may leak through the
filler plug if exposed to high temperatures.
Leaking igniters can be determined by the
presence of smoke and/or flame or by the
presence of coarse white material on the
igniter. If any of these conditions are ob¬
served, notify explosive ordnance disposal
(EOD) personnel immediately.

1-240

Change 5

T.O. 1F-4C-34-1-1

M23 or AN-M23A1 IGNITER

M23 or AN-M23A1
-IGNITER-

1. FUZE ADAPTER
M23 ONLY

2. BODY

3. FILLING

4. MOUNTING THREADS

5. FILLER PLUG

Figure 1-117

FMU-54/B TAIL FUZE

The FMU- 54/B tail fuze is a mechanically operated
retardation sensing device with a predetermined
arming delay of 0.75 to 3.50 seconds, settable in 0.25
second intervals. The fuze is used for the tail fuze
well of only the M117, and MK 82 bombs equipped
with high drag (retardation) fins. Upon release, the
fin causes rapid deceleration of the bomb, initiates
the fuze arming cycle and provides a safe escape
distance from delivery aircraft. In the event of fin
malfunction, the fuze will not arm. A properly armed
fuze will function upon impact when a G weight re¬
leases the spring-loaded firing pin. The fuze is me¬
chanically initiated by a lanyard connected to the py¬
lon swivel. As the bomb falls away, the lanyard pulls
the fuze lanyard engaging shaft, thus releasing the
fuze components to operate if proper retardation is
experienced. The lanyard assembly is routed such
that the lanyard will go with the bomb after perform¬
ing its function.

Assembly and Installation

Upon removal of the tail fuze well plug, feed the free
end of the lanyard through the tail fuze well, into the
conduit, and out the bomb charging well. The lanyard
assembly is seated in the fuze well. The lanyard
lock is installed in the bomb charging well and held
in place by the retaining ring. The lanyard is fed
through the circular portion of the swivel assembly
and through the key lock holes in the lanyard lock.

The fuze is removed from the container, safety pin
pulled (waterproofing pin inserted in its place) and
inserted into the fuze well. Slight movement of the
lanyard, protruding through the charging well indi¬
cates that the fuze has been seated. Rotate timing in¬
dicator counterclockwise one full turn and set to de¬
sired setting. If desired setting is passed, continue
CCW rotation to the predetermined time setting. In¬
stall the rubber bumper in the bomb end cap recess
and install the end cap.

Note

After fuze installation, the accompanying red
warning tag should be filled in and attached to
the bomb.

Compatibility

The FMU-54/B fuze is compatible with the tail fuze
well of only the Ml 17, and MK 82 GP bombs that are
configured with high drag fins. Bombs using high
drag fins but intended to be dropped in the low drag
mode, require fuzing other than the FMU- 54/B.

Normal Operating Sequence and Modes

As the bomb falls away from the aircraft, the lan¬
yard pulls the fuze lanyard engaging shaft, thus re¬
leasing the fuze components to operate. With a re¬
tardation force of 3.5 ± 0.5G, the commit weight
frees the main G-weight which moves to its full
travel. The G-weight is connected to the timing
block by two springs which pull the timing block
through a delay assembly. Upon reaching the end of
its travel, the timing block releases the timer verge
locking pin allowing the timer to operate, thus arm¬
ing the fuze in the pre-set period of time. The tim¬
ing block takes 0.6 seconds to reach its full travel
and if at any time during this 0.6 seconds retardation
is lost, the G-weight reverts to its original position
and does not arm the fuze. If the fuze has not armed
prior to impact, a failsafe G-weight functions upon
impact and allows a pin to block the path of the slider
assembly to prevent arming. If the fuze has become
armed during drop and if the firing pin G-weight is
unlocked upon impact, the G-weight will slide for¬
ward to release the spring-loaded firing pin. The
firing pin strikes the detonator and the explosive
propagation continues through the lead cups to the
booster.

Special Safety Features

a. The fuze requires a 0.6 second sustained G load¬
ing in the front to rear direction in order to arm. An
initiated fuze can be subjected to repeated impacts
from the front but will not arm unless the impacts
are of 0.6 seconds or longer duration.

b. If fin failure occurs during fin opening, the re¬
tardation time is insufficient to arm the fuze.

c. If the fins have not functioned properly, the fail¬
safe G-weight will function upon impact and prevent
arming during retardation experienced duringimpact.

Operating Restrictions

The minimum release airspeed is 350 knots CAS for
bombs used with the FMU-54/B Fuze. The maximum
release airspeed is the limit imposed by the bomb
and aircraft. Refer to T.O. 1F-4C-1.

Safe Escape

Safe escape criteria must be observed in the selec¬
tion of FMU-54/B arming delay settings. Even though
the fuze arming delay can be set to a value as low as
0.75 sec, a minimum setting of 2.5 sec must be used
to assure safe escape during low level operations.
Considering the MK 15 Mods 1, 2, 3 retarder (MK 82
Snakeye 1) and MAU-91A/B, B/B retarder (M117
Ret) opening times, this would require the selection
of release conditions which will provide a minimum
bomb time-of-flight of 2.8 sec. Fuze Arming and

Change 5

1-241

T.O. 1F-4C-34-1-1

Safe Escape tables which list the altitudes required
for safe escape and FMU-54/B fuze arming (for the
2.5 second arming delay setting) are listed in sec¬
tion VI.

To assure safe escape in the event of a pre¬
mature airburst detonation, the FMU- 54/B
arming delay setting must be a minimum of
2.5 seconds.

Note

• The selected arming delay setting should be
recorded on the red warning tag which is
filled in and attached to the bomb when the
loading is completed. This should be checked
by the aircrew during the pre-flight of the
aircraft.

• Since the fuze settings are not visible to the
pilot for inspection, the munitions handling
and loading personnel must be carefully
briefed on the required settings and the red
warning tag procedures.

FMU-54A/B TAIL FUZE

The FMU-54A/B is a modified version of the FMU-
54/B (figure 1-117A). The major differences be¬
tween the two fuzes are in the selectable safe sep¬
aration times, and in provisions which enable the
FMU-54A/B to be used in conjunction with a MK-43
Target Detecting Device (TDD). The fuze fits into
the tail fuze well of Ml 17 and MK-82 bombs equipped
with a high-drag (retardation) fin. A safe-separation
timer provides ground-settable delays of 2.5 to
6.0 seconds, settable in 0.25-second intervals.

The FMU- 54A/B fuze can be used either alone or in
conjunction with a MK-43 Target Detecting Device
(TDD). When both units are used, the TDD electri¬
cally activates the FMU-54A/B fuze at a set function
altitude above the ground. However, if the TDD is
not used or does not provide a firing signal, the
FMU-54A/B fuze will detonate the bomb at impact.
During an armed release, the FMU-54A/B functions
as follows:

a. When the cord assembly that is attached to the
arming solenoid stretches to its elastic limit, the
swivel and link assembly fails allowing the lanyard
to retract into the internal plumbing and fall with
the bomb, thus initiating the fuze arming cycle. The
D ring of the swivel and link assembly remains with
the aircraft.

b. The fin release pin is then withdrawn from the
fin retaining band latch.

c. When the fin drag plates open, an arming wire
attached to one drag plate is withdrawn from the
striker rod in the MK-43 TDD. The fin drag plates
provide stability and deceleration during bomb
descent.

d. Sustained retardation of 4.0 G for 0.6 second
causes the retardation sensor in the fuze to complete
the sensing cycle and start mechanical timing se¬
quence of 2.5 to 6.0 seconds arming time. At the
end of the preset arming delay, the rotor release
shaft permits the spring loaded rotor to move so
that the detonator in the rotor is in line with the
firing pin and the explosive lead in the fuze housing.
The electrical detonator in the rotor is also in con¬
tact with the electrical leads to the MK-43 TDD.
When the rotor is in line, the fuze is fully armed.

e. The MK-43 TDD is initiated by withdrawal of
the arming wire from the striker rod. The spring
loaded striker rod ignites the thermal battery
through an electric pyrotechnic match. The thermal
battery reaches its operating voltage in approxi¬
mately 2 seconds. As the bomb approaches the target
the interaction between the emitted and reflected
radio frequency energy causes a doppler signal to
appear at the oscillator detector. This signal is
then applied to the target signal amplifier to be am¬
plified sufficiently to trigger the thyratron in the
firing circuit. Energy is thus applied to the electric
detonator in the FMU-54A/B fuze and the bomb
detonates.

f. If the FMU-54A/B fuze is used alone or the MK-
43 TDD fails to function, the spring loaded firing pin
initiates the detonator at impact.

MK-43 TARGET DETECTING DEVICE

The MK-43 Target Detecting Device (TDD) is an
electronic proximity sensor that provides an electri¬
cal signal to detonate the FMU- 54A/B fuze (figure
1-117A). The TDD fits into the nose fuze well of

Change 7

1-242

T.O. 1F-4C-34-1-1

■

— SAFETY CLIP
(Retained for Electrical
Arming, Removed for
Mechanical Arming)

FMU-54A/B

MK 43 TDD

4C—34-1 —1 -(221)

Figure 1-117A

1-242A

Change 7

T.O. 1F-4C-34-1-1

Ml AND MW FUZE EXTENDER

ALUMINUM TUBE

ADAPTER BOOSTER ■

M904 FUZE

LOOP CLAMP

4C-34- 1-1—(209)

Figure 1-118

the Mil7 series and MK-82 series bomb. The TDD
contains no explosive components. The nominal
function height for the MK-43 is 16 feet.

The MK-43 TDD consists of a cylindrical metal body
with a dark green plastic nose cone attached to the
forward end. The battery initiating striker rod pro¬
trudes from the nose cone. This spring loaded
striker rod protrudes from the nose cone. This
spring loaded striker rod is held in place by a safety
clip. A receptacle for ah electrical connection is
located at the rear of the cylindrical body. The TDD
is initiated by withdrawal of the arming wire from
the striker rod. This occurs when the high drag fin
is deployed shortly after release. The spring loaded
striker rod ignites the thermal battery through an
electric pyrotechnic match. The thermal battery
reaches operating voltage in approximately 2 sec -
onds. The target signal amplifier output is fed to
the radio frequency oscillator detector where
pulsed radio frequency energy is radiated outward
in a lobol pattern. As the bomb approaches the
target, the interaction between the emitted and re¬
flected radio frequency energy causes a doppler
signal to appear at the oscillator detector. This
signal is then applied to the target signal amplifier
to be amplified sufficiently to trigger the thyratron
in the firing circuit. Energy is then applied to the
electric detonator in the FMU- 54A/B bomb fuze
which detonates the bomb.

FUZE EXTENDERS

M-l AND M1A1 FUZE EXTENDERS

The fuze extension devices (figure 1-118) are physi¬
cally compatible with T45 series nose adapter boost¬
er and any bomb which will accept M904E1, E2, E3
nose fuzes. It consists of a burster support and a
burster assembly. The burster support is a steel
tube 2.375 inches outside diameter which has a male
thread at one end for attaching to the bomb, and T45
series nose adapter/booster and a female thread at
the other end to receive nose fuze. The burster as¬
sembly consists of an asphalt impregnated chipboard
which has a recessed metal cap crimped to one end
and a plain metal cap cemented to the other. The
tube is filled with cast tetrytol. The overall length
of the burster support is 36.72 inches; burster as¬
sembly, 35.96 inches; designated size, 36 inches.
The fuze extenders are authorized for use with the
M118 GP, MK 82, MK 83, and MK 84 LDGP bombs.
Only the M904 fuze is recommended. Three fuze
extenders are available in 18-inch, 24-inch, and
36-inch lengths.

Until ballistic testing of the fuze extenders is ac¬
complished and published, the existing bombing
tables, fuze arming data and safe escape data should
be used. Refer to T.O. 1F-4C-1 for load configura¬
tion and External Store Limitations on the bombs
authorized to use the fuze extenders.

1-242B

Change 7

T.O. 1F-4C-34-1-1

TRAINING WEAPONS AND EQUIPMENT

SOu-20/A, A/A, B/A, BOMB AND
ROCKET DISPENSER

The SUU-20 practice bomb and rocket dispenser
(figure 1-119) is an externally mounted pod which
has both rocket launching and practice bomb ejection
capabilities. Dispenser statistics are listed below.

a. Length: 122 inches

b. Width: 19.3 inches

c. Weight: 465 lbs. approximate (loaded with six
25-lb. practice bombs and four 2.75-inch
rockets). Empty weight: 241 lbs.

d. Drag index: Full: 3.1

Empty: 3.7

The dispenser is designed to carry six practice
bombs and four 2.75 inch FFAR rockets. The six
practice bombs are carried in a recessed open bay
and held in individual bomb ejector guns by retention
arms and sway braces. The rockets are contained
in four launch tubes, two tubes located on each side
of the dispenser. The two left side launch tubes (1
and 2) are shown in figure 1-119.

The general differences between the various series
dispensers are:

| a. The SUU-20A/A and B/A have strengthened hard
back to accept the force of an ejector foot when jet¬
tisoned.

b. The SUU-20A/A and B/A employ the use of
ejector gun safety pins and SUU-20/A uses bomb re¬
taining locks (figure 1-119) to safe the practice bombs
prior to flight.

c. The SUU-20A/A and B/A have improved sway
brace assemblies.

The bomb ejector gun is a rod-and-piston assembly,
operated within a breech housing and driven by gas
pressure that is produced from an electrically fired
ejector cartridge. An ejection velocity of 21 feet per
second for a 25-pound bomb is produced. A typical
breech housing with a lock type safety pin installed
is shown in figure 1-119. One end of the safety pin
retaining cable is permanently secured to the dis¬
penser and the other end containing the lock pin is
inserted into the breech housing; therefore, when the
breech mechanism and cartridges are not installed,
the safety lock pins will be clearly visible as shown
by the side view of the dispenser. On the SUU-20/A,
additional bomb ground safety is obtained by bomb
retention locks which are hooked to one retention
arm, closed around the bomb, and secured with a
red flagged safety pin to the other retention arm.
Also, the bomb/rocket electrical circuit is safetied,
thus preventing inadvertent stores release through
activation of the dispenser intervalometers. This is
accomplished by inserting a red flagged safety clip
into the dispensers electrical circuit. When in¬
stalled, the electrical safety flag will be visible at
the rear end of the dispenser.

A typical preflight on the SUU-20/A dispenser re¬
veals seven red flags and, if the ejector cartridges
are not installed, six safety lock pins hanging from
the bottom of the dispenser.

Note

Observation of the safety lock pins depends
on whether the cartridges have been installed
in the bomb ejector guns.

DISPENSER INTERVALOMETERS

Figure 1-119 shows two similar intervalometers lo¬
cated on the underside of the dispenser forward of
the numbers 1 and 3 bomb dispenser stations. Note
the rocket intervalometer is forward of the number 1
station while the bomb intervalometer is forward of
the number 3 station. The only difference in the two
intervalometers is the number of stepping positions
for the ripple and single modes of operation. These
positions conform to the number of bomb and rocket
positions which are 6 and 4, respectively.

The 28 volt dc power required for dispenser opera¬
tion is furnished by the weapon select switch and the
master arm switch. When the master arm switch is
in the ARM position, the bomb button transfer relay
is energized, which routes the pickle signal from
the bomb button to the aircraft intervalometer. Plac¬
ing the weapon select switch to RKTS & DISP ener¬
gizes a relay within the SUU-20 dispenser. This
relay eliminates the requirement that both bomb and
rocket circuitry be available at the dispenser carry¬
ing station (figure 1-120). This is accomplished by
directing the firing pulses through this relay to the
appropriate dispenser intervalometer. With the
weapon selector knob on the desired mode, the dis¬
penser relay completes the circuit to either the bomb
or rocket intervalometer.

For clarity of text the modes of operation are
covered in a SINGLE, RIPPLE and SALVO sequence
and it is assumed that the initial release require¬
ment is bombs, then rockets. It is also assumed the
aircraft is configured with two dispensers, one
mounted on each inboard wing station (stations 2
and 8).

The intervalometer modes of operation must be se¬
lected prior to flight. During preflight, the inter¬
valometers are in the SAFE position just preceding
the desired mode of operation. For example, if the
mission requires SINGLE MODE operation the inter¬
valometers would actually be set on SALVO SAFE.
Therefore, when the intervalometers are armed, the
switch will not track through any other mode. The
SINGLE ARM position must be selected prior to
flight.

Note

In the event a full bomb or rocket load is not
carried, the bombs and rockets should be
loaded in a manner that is compatible with
the release sequence.

Change 7

1-243

SUU-20/A, A/A, B/A DISPENSERS >W

I - - - ■—, ... -. . ______

SAFETY CIRCUIT
DISCONNECT SPRING

[CARTRIDGE SAFETY

SUU-20/A BOMB RETAINING LOCK FLAGS (6)

OR S UU-20 A/AjB/ A EJECTOR GUN SAFETY PIN FLAGS . Wl Hl

SUU-20/A EJECTOR ASSY
CARTRIDGE BREECH NOT INSTALLED

INTERVALOMETERS

SUU-20A/A EJECTOR ASSY
CARTRIDGE BREECH INSTALLED

CARTRIDGE
RETAINER
SAFETY CABLE

CARTRIDGE

EJECTOR

BRACE t

BOMB

RETAINING

LOCK

TOP VIEW

SUU-20B/A EJECTOR ASSY

SAFETY PIN
ACCESS

SUU-20A/A, B/A SAFETY PINS

EJECTOR

BREECH

Figure 1-119

T.O. 1F-4C-34-1-1

BOMB

BUTTON

NUCL.

FRONT COCKPIT A

AFT COCKPIT A

MASTER

ARM

SWITCH

STATION

SELECT

SWITCH

RKTS 6/0 BOMBS
WEAPON

SELECT

SWITCH

6^ol

ROCKET

INTERVALOMETER

ROCKET FIRE

SUU-20 A DISPENSER

RIPPLE

AIRCRAFT

INTERVALOMETER

S SINGLE

LEFT ,
WING j

, RIGHT
f WING

STATION

SELECT

RELAYS

BOMB

f INTERVALOMETER

T~ BOMB RELEASE

4C—34— 1 — 1 — (121

Figure 1-120

In addition to the single, ripple and salvo modes that
are selectable within the SUU-20 dispenser, the
aircraft cockpit selections are also available. Use of
the weapon select knob on BOMBS/SINGLE/TRIPLE
or RIPPLE and the aircraft intervalometer settings
provide inflight cockpit selectivity. To obtain the ca¬
pability, set the bomb intervalometer in the SUU-20
to BOMB SINGLE.

The SUU-20 intervalometer requires approximately
50 to 75 milliseconds to step from one station to the
next. When the aircraft intervalometer is set to 60
milliseconds, the second pulse may reach the dis¬
penser prior to stepping to station two. Therefore,
if BOMBS TRIPPLE (F-4D/E) is selected in the
cockpit, only two bombs may release from the dis¬
penser. When BOMBS RIPPLE is selected, the
bombs in the SUU-20 will release but the time in¬
tervals are twice that selected. To preclude these

occurrences, use 0.10 and 0.14 aircraft intervalom¬
eter settings.

WARNING

(F-4C only) If the SUU-20 containing both
rockets and bombs is aboard, and an empty
TER is aboard the opposite station (2 and 8),
applying the bomb release signal in a BOMBS
PAIRS mode may also launch a rocket. The
stepper circuits in the TER cause a feed¬
back pulse which may be of sufficient dura¬
tion to cause the rocket launch.

Use of the cockpit selection of RKTS & DISP/RIPPLE

is authorized and may be used. However, the same

Change 7

1-245

T.O. 1F-4C-34-1-1

TOP VIEW

I 4C—34-1-1-022)

BOMB

DRAG NUMBER ....

. ... 3.3

WEIGHT EMPTY. . . .

. ... 470 POUNDS

LENGTH.

. . . . 13 FEET

DIAMETER.

. . . . 17 INCHES

i CIRCUIT BREAKER L

i MODE
, SWITCH j

SAFETY
i PINS (6)

<§■

| [ PRESS TO RESET )

fgjAUTOMATlCfg)

manOai

Figure 1-121

firing interval delay is present. Therefore, use air¬
craft intervalometer setting of 100 and 140 millisec¬
onds only and set the SUU-20 rocket intervalometer
to ROCKET SINGLE.

SINGLE MODE OPERATION

Single mode operation allows the AC to eject one
bomb, or fire one rocket at a time. The AC has the
option of selecting a single bomb release from the
left dispenser, then the right dispenser, or a simul¬
taneous single release from both dispensers (pairs).
The release sequence for both bomb and rockets is
shown in figure 1-119.

RIPPLE MODE OPERATION

The ripple mode of operation allows the AC to re¬
lease bombs or fire rockets in a fixed 100 millisec¬
ond interval. The AC also has the option of selecting
ripple capabilities from the left dispenser, then the
right dispenser or both dispensers at the same time.
The release sequence for both bombs and rockets is
shown in figure 1-119.

Note

The AC must hold the bomb button depressed
for the duration of the RIPPLE sequence,
which is approximately half a second.

SALVO MODE OPERATION

The salvo mode of operation gives the AC the capa¬
bility of releasing all bombs or all rockets simulta¬
neously. The dispenser relay directs the firing pulse
through the dispenser (BOMBS or ROCKETS) to si¬
multaneously release all six bombs or fire all four
rockets.

SUU-21/A BOMB DISPENSER

The SUU-21/A bomb dispenser (formerly the MN-1A
dispenser) (figure 1-121) contains six, spring-loaded
ejector mechanisms, permitting up to six bomb re¬
leases during one sortie. The act of loading a prac¬
tice bomb forces the ejector plunger upward, com¬
pressing a spring until toggle arms snap into a cocked
position around the bomb, securing it to the ejector.
As the ejector operates (cocking or releasing), an
indicator pin extends from the side of the dispenser
near the ejector being loaded, then retracts within
the dispenser contour. A red flagged stop guard is
inserted into a slot over the indicator pin hole to
prevent release of a bomb-loaded ejector. The guards
must be removed prior to flight. The bombs are re¬
leased singularly in sequence determined by a circuit
selector within the dispenser, but this release se¬
quence can begin with any of the ejector positions by
manually positioning the rotary switch on the dis¬
penser relay box prior to takeoff.

1-246

Change 7

T.O. 1F-4C-34-1-1

Note

* For inboard carriage capability, the SUU-
21/A dispenser is modified in accordance
with T.O. 11N-PD-SUU-21/A-504.

• Some organizations may have modified
SUU-21 dispensers, which are operated
through the converntional weapons controls

| on the pedestal panel (F-4C/D/E). The dis¬
pensers are carried only on the inboard
stations. Aircrew procedures for these dis¬
pensers are available in section II.

The 28 volt dc current required for dispenser oper¬
ation is furnished by the DCU-94/A control-monitor,
and the aircraft release systems. Dispenser conti¬
nuity is monitored, and bomb bay door operation is

Change 7

1-246A/(1-246B blank)

T.O. 1F-4C-34-1-1

controlled through the DCU-94/A control-monitor.
Placing the option selector knob to SAFE, and then
depressing the bomb test button illuminates the loaded
station WARN light to verify aircraft/dispenser elec¬
trical continuity. (Assume here that the dispenser
doors are closed.) This check verifies that only two
of the electrical connectors are properly installed.
The remaining (rack primary) plug, which powers the
dispenser release relay at bomb release, is not in¬
cluded in the bomb test circuit. If the doors are open
when the AC selects SAFE as described, the doors
will close - regardless of the position of the station
select switch and the nuclear store consent switch.

To power the door-open and automatic-close func¬
tions, however, the loaded station select and con¬
sent switches must be energized and the DCU-94/A
option switch must be positioned to GND or AIR. The
consent switch must be placed on REL/ARM. This
directs 28 vdc main bus power to the door-open side
of the door actuator. The WARN light flashes during
door travel, and illuminates steadily when the doors
fully open. When the doors fully open, an interlock
switch is closed, completing the dispenser release
circuit. The AC energizes the master release lock
switch and selects the desired bombing mode to re¬
lease a single bomb.

To illustrate the SUU-21/A door functions with re¬
spect to switching procedure on the DCU-94/A, sup¬
pose the aircrew enters the cockpit for the mission
while the loaded dispenser doors are open. Also,
suppose that all armament switches are deenergized
with the exception of the option selector, which is
positioned on either SAFE, GND or AIR. As soon as
the 28 volt dc essential bus is energized (external
power applied or during engine start) the dispenser
doors will close. To keep the doors open, the air¬
crew must select either: (1) the OFF position on the
option selector; or (2) the GND or AIR position and
place the applicable station select switch forward,
and place the consent switch to REL/ARM prior to
applying essential bus power. Then, as power is
available in either case, the pilot selects SAFE to
close the doors. These functions are independent of
the position of the mode switch located on the dis¬
penser relay box which is discussed below.

AUTOMATIC MODE

The automatic door-close function is selected by the
mode switch on the dispenser relay box (figure 1-121).
When the bomb button is depressed, with the mode
switch positioned on AUTOMATIC, power from the
bomb button energizes relays that remove voltage
from the door-open coil of the door actuator, and the
doors begin to close automatically as a single bomb
is released. The WARN light flashes as the doors
close, and goes off as the doors fully close. The AC
reopens the doors by moving the option switch (from
GND) to SAFE, and back to GND. This procedure is
performed after each bomb release to reopen the
doors. The AC may close the doors any time (without
releasing a bomb) by selecting SAFE on the option
switch.

Note

The aircrew may close the doors by placing
the nuclear store consent switch on SAFE, or
the loaded station select switch to the AFT
position. If the consent switch is used, the
WARN light will remain illuminated through¬
out the door cycle. If the loaded station switch
is used, the light will function normally.

MANUAL MODE

With MANUAL selected, those relays which govern
automatic operation (above) are not energized as
bomb release voltage is applied. Hence, the doors
remain open until the AC elects to close them by se¬
lecting SAFE on the DCU-94/A.

Note

Although the dispenser doors may remain
open continually, the unit is susceptible to
low frequency vibrations that may cause
structural damage. When operating in the
manual mode, it is recommended that the
doors remain open only while the aircraft
is on the bombing range, and closed during
all other periods of flight. Each dispenser
should be inspected periodically according
to procedures specified by the appropriate
command.

INTERLOCK CONTROLS

The dispenser doors are opened and the release cir¬
cuit is unlocked by first positioning three interlock
switches. With the option switch on SAFE, the loaded
station select switch is placed forward, and the nu¬
clear store consent switch is placed to REL/ARM.
The doors will now open by selecting GRD on the
option switch. The REL position of the consent switch
serves no purpose with the dispenser aboard. These
functions receive 28 vdc power through the AMAC
circuit breaker.

The fire circuit is unlocked by actuating the consent
switch and the station select switch as indicated
above, and then by moving the master release lock
switch to the forward position. The loaded station
UNLOCK light now illuminates, indicating the readi¬
ness of the release circuit. The AC may release a
single bomb button, provided a specific bomb mode
has been selected on the bomb control panel.

Note

The UNLOCKED light will come on if the
nuclear store consent switch is in REL; how¬
ever, the REL/ARM position must be engaged
to complete the arm circuit and open the bomb
bay doors.

DCU-94/A CONTROL-MONITOR

The DCU-94/A control-monitor (figure 1-43) is lo¬
cated on the AC right console. Power is available for

1-247

T.O. 1F-4C-34-1-1

the panel from the 28 vdc essential bus. The panel
contains controls that energize the bomb arming (dis¬
penser door opening) circuit, and the bomb release
circuit.

The option selector knob has four positions: OFF,
SAFE, BOMB-GRD, and BOMB-AIR. The AIR posi¬
tion may be ignored for non-nuclear delivery; select¬
ing AIR will perform the same function as the GRD
position. The option switch is guarded by a control
arm limiting its movement to the OFF and SAFE po¬
sitions. The control arm must be moved from OS
(OFF-SAFE) to S-ARM (SAFE-ARM) before the knob
can be positioned to GRD. In OFF, all power is re¬
moved from the dispenser. Selecting the SAFE po¬
sition powers the centerline WARN light bomb test
circuit, provided that the dispenser stub cable as¬
sembly is properly connected. The GRD position
energizes the door actuators, provided the interlock
controls are energized. When the doors fully open,
the CL Warn light illuminates steadily.

With the SUU-21/A dispenser aboard, selecting die
SAFE position powers the dispenser manual door-
close circuit, and the dispenser/Wam light moni¬
toring functions. The GND (and AIR) position directs
main bus 28 vdc power to the door-open and auto¬
matic door-close circuits, provided the interlock
controls are energized.

Note

An attempt to force the movement of the op¬
tion selector control arm can damage the
option selector/control arm assembly and
render the locking functions useless. The
control arm should be positioned only when
the option selector is in the SAFE position.

The CL UNLOCK light monitors the CL fire relay;
the wing station UNLOCK lights monitor the MAU-12
unlock solenoids. The SUU-21 release circuit is
energized through the following controls.

a. Master release lock switch - FORWARD

b. Wing/CL station select switch - FORWARD
(1) Wing station UNLOCK light - ON

c. (P) Nuclear store consent switch - REL/ARM
(1) CL station UNLOCK light - ON

If the MAU-12 inflight lockout bolts are installed,
the wing station UNLOCK lights are illuminated con¬
tinuously.

Note

• If other munitions are loaded on the CL sta¬
tion with the SUU-21 on a wing station, a CL
station select switch guard should be installed
on the DCU-92/A to prevent inadvertent jetti¬
son of the CL load. Also, switch guards may
be applied to the wing stations.

*The SUU-21/A release sequence when all
stations are selected is as follows: CL,

LI, RI.

The lamp test button is a pushbutton switch that per¬
mits a functional check of all the warning and un¬
locked lamps on the DCU-94/A control-monitor. The
button is functional when 28 vdc essential bus power
is available.

The bomb test button is a pushbutton switch used to
check electrical continuity between the dispenser
and the DUC-94/A control-monitor. The button is
functional to perform the continuity check when the
option selector is in the safe position, and with 28
vdc essential bus power available to the DCU-94/A
panel.

PRACTICE BOMBS

BDU-33 SERIES PRACTICE BOMBS

The BDU-33 Series Practice Bomb (figure 1-122) has
an elongated, tear-drop shaped body and a fin assem¬
bly welded to a center tube, A conical after body is
welded to the center tube and roll crimped into two
grooves on aft end of bomb body. A firing pin assem¬
bly, signal cartridge and/or signal cartridge and
inertia tube are inserted into the bomb and retained
by a cotter pin. Upon impact the firing pin strikes
the primer of the signal cartridge, detonating the sig¬
nal producing a flash and smoke cloud to provide a
visual point of impact.

Difference Data

BDU-33/B - Shrouded Fin, Signal Cartridge and fir¬
ing pin assembly inserted in nose end of practice
bomb.

BDU-33A/B - Cruciform type Fin, firing pin assem¬
bly, signal cartridge and inertia tube inserted in tail
end of practice bomb. The ballistics differ suffi¬
ciently to require a separate set of bombing tables in
T.O. 1F-4C-34-1-2, one set for the SUU-20/A bomb
and rocket dispenser and one set for the SUU-21/A
bomb dispenser.

BDU-33B/B - Same as BDU-33A/B with exception of
safety device (cotter pin and tag) which is inserted
between firing pin and signal cartridge during buildup
and handling, prior to flight.

Physical Characteristics

a. Weight 24 pounds

b. Length 23 inches

c. Diameter 4 inches

MK 106 PRACTICE BOMB

The high drag MK 106 practice bomb (figure 1-122) is
constructed of steel, weighs 5 pounds, is 19 inches
in length and 4 inches in diameter. The bomb is com¬
posed of an inner cylinder, an outer cylinder, and fin
assembly. The bomb utilizes the MK 4 Mod 3 bomb
spotting charge installed into the inner cylinder. A
box type fin assembly, consisting of four metal vanes
welded together, is welded to the aft end of the inner
cylinder. One of two indexing holes in the bomb mate
with the indexing pin in the bomb ejector saddle pad
when the bomb is loaded in the SUU-21/A dispenser.
Each has a plunger safety clip which must be removed
before flight.

Note

The MK 106 practice bomb is authorized for
use with the SUU-20/A practice bomb and
rocket dispenser after the ejector foot pad
is modified to prevent distortion of the bomb
during ejection.

1-248

Change 1

PRACTICE BOMBS

BDU-33A/B

25 POUNDS

MK 106

5 POUNDS

T.O. 1F-4C-34-1-1

UMBILICAL TEST SET (UTS)

AN/AWM-19

The airborne umbilical test set (UTS) AN/AWM-19
(figure 1-123) provides inflight checkout of the
AIM-7D/E missile and the fire control system. The
UTS becomes an integral part of the missile: the
missile warhead is removed and replaced by the UTS,
which is identical in size to the warhead. The test
missile containing the UTS can be loaded on any mis¬
sile station to checkout that particular station. The
launcher and eject cartridges are removed to pre¬
clude jettison and launch of the test missile. The
UTS provides nine indicators which can be used for
crew evaluation. To provide a complete evaluation
requires the use of a scope camera. The scope cam¬
era should be used to evaluate the performance of the
crew in acquiring and tracking the target and method
of flying the aim dot. The UTS would record the
proper operation of the various switches required for
launch. The UTS checks out the wiring continuity to
the missile station, the presence and level of signals
from the FCS and aircraft, and the firing relay op¬
eration. Four test missile firings can be made for
each test missile aboard. The first two firings are
made on a live target. The third firing is accom¬
plished in BIT 6, and the fourth firing is accom¬
plished in BIT 3. The third and fourth BIT firings
are made to check the tester operation, and to vali¬
date indications received during the first two test
firings. The trigger switch is held for 5 seconds to
culminate each test firing. If more than one test
missile is aboard, the normal missile firing sequence
is observed (live AIM-7D/E are not usually carried
when a test missile is aboard). The missile status
panel SELECT and READY lights must be noted by
the AC to determine the presence of proper pseudo
and rear rf signals (missile tuned). The launch sig¬
nal is sent to the UTS for evaluation when the trigger
switch is depressed. Upon completion of flight, the
UTS is inspected to determine faulty operation of the
circuits or capability of the systems.

Three separate rows of event indicators are provided
to allow independent testing of certain signals when
operating against a live target or in BIT 6. BIT 6
supplies inputs to the FCS which are sufficient to
properly check almost all functions going to the UTS.
However, there are two functions (switch after boost
and sweep select) which cannot be properly checked
in BIT 6. Therefore, a fourth firing in BIT 3 is re¬
quired to check out these functions properly: a
fourth row of indicators accommodates these signals.
The magnetic latching type event indicators, once
energized, remains energized after loss of power.

The appearance of a white indicator confirms a go
condition. The SWP SEL and SW AFT BOOST are
functional with the AIM-7E only and will not indicate
when an AIM-7D is aboard.

The presence and level of the head aim, english bias,
roll command, sweep control and missile recycle
signals is checked by their respective voltage com¬
parators. The preset high and low-limit comparison
signals are supplied to each comparator through a
missile station select switch which is set to corre¬

spond to the actual aircraft missile launching station
under test. The presence of a simulated doppler
signal is checked by a doppler detector. Presence
and amplitude of the motor fire and eject and jettison
signals are checked by their respective threshold
detectors. Missile power is processed through a
three-phase fault detector which checks for proper
amplitude. The remaining signals (hub hydraulic
actuate, klystron tuner limit and AFC, altitude 1
and 2, and Grounds A and B) await +28 vdc launch
signal in order to energize their event indicators.

The UTS indicator and controls are shown in figure
1-123. The first eight indicators (left of the vertical
line) and the Swp Sel indicator (fourth row) are used
for aircrew evaluation. Figure 1-123 states the pur¬
pose and use of each UTS indicator and control.

RADAR SCOPE CAMERA

The radar recording system is comprised of a still
picture camera, a periscope assembly, and a camera
control (figure 1-124). The system automatically
photographs the radar scope display, keeping a con¬
tinual record of radar presentations during the mis¬
sion. The photo-optical arrangement and the design
of the periscope assembly is generally shown in fig¬
ure 1-125. The functions of these units are as follows:

a. To reflect the radar display to the camera and
transmit the display to the pilot.

b. To attenuate any light from an outside source
that may enter the periscope and degrade the quality
of picture to be taken.

The optical theory is not discussed here, but in gen¬
eral, the polarized lenses enable the pilot to adjust
the intensity of the video display to a desired level,
while the amount of light reaching the camera does
not vary. The radar intensity control is set to a
maximum for camera operations, and then the pilot
rotates the outer filter on the periscope to obtain a
desired video level.

The photo-optical system records the radar display,
and also records various fire control system func¬
tions by momentarily illuminating small correlator
lights in the camera. With the radar operating in
the search mode, a picture is automatically taken at
the end of each B-azimuth sweep or MAP PPI sweep.
The pulse that momentarily opens the shutter to ex¬
pose the film is synchronized with the antenna azi¬
muth position. During lock-on, track, boresight, or
BIT 2, 3, 5 or 6 operations, where there is no an¬
tenna scan, the pictures are taken at a rate deter¬
mined by the position of the rate selector knob, plac¬
arded FPS (frames per second), on the camera con¬
trol panel (from 2 to 6 frames per second).

Seven correlator lights, inside the camera, are con¬
nected to fire control system and armaments system
circuits. When illuminated, the lights expose small
dots along the edge of the film to mark an occurrence
within the fire control or armament system. The
position and meaning of each light - when illuminated-
is shown in figure 1-126.

1-250

T.O. 1F-4C-34-1-1

UMBILICAL TEST SET AN/AWM-19

<OR,

AIRCREW EVALUATION

AC FUNCTION CHECKED

UTS INDICATOR

OTHER INDICATIONS

REMARKS

1. Missile power sw - RADAR STBV

2. Missile arm sw - SAFE

3. Missile select sw - RADAR

These functions are in¬
dicated as noted in items G and 7.

4. Missile interlock sw - IN

Interlocks must be in for
meaningful results.

5. Missile power sw - PWR ON

H LIMIT
il AFC

SELECTED light ON

No flag if HEAT is selected.

6. Missile arm sw - ARM

□ SIM OOP

READY light ON

7. Missile arm sw positioned to ARM
in proper sequence.

Q MSL RCY

Flag will appear if ARM was
selected after SELECTED
light ON. No flag if ARM
was selected earlv.

8. Trigger sw. - DEPRESS

5 SECONDS.

D MSL PWR
□ HYD ACT

H MOT FIRE

O EJECT JETT

SELECTED and READY
lights OUT

Lights go out after trigger
is released. No flag if

HEAT was selected.

9.AC Technique

Scope Camera

Will evaluate performance
in flying the aim dot etc.

PILOT FUNCTION CHECKED

No flag on Qfl or Q
if MISSILE FIRING
circuit breaker is OUT

1. Circuit Breakers - IN

2. Radar power sw - OPR

Scope Camera

3. Gate sw - NAR

□ SWP SEL

Only one flag available,
during the first two firings.

4. Radar mode sw - RDR

Scope Camera

5. Polarization sw - CIR 1 or LIN

No indication available.

6. Target tracking

Scope Camera

7. Target Lock-on

Scope Camera

Will show a steady ASE
circle if HEAT is se¬
lected. or a varying ASE
circle if RADAR is selected.

F4-34-I-492

Figure 1-123

1-251

T.O. 1F-4C-34-1-1

DRSC PANEL

F-4E

Figure 1-124

THE CAMERA

The camera uses a standard 16 mm Kodak film mag¬
azine with 50 foot capacity. The film magazine is
loaded into a receiver on the inner face of the cam¬
era door (figure 1-125). With the film properly in¬
serted and the camera door closed, the camera gear
train engages the magazine drive assembly. Also,
the magazine pushes against a switch - opening the
circuit to the film remaining (amber) light and clos¬
ing the circuit to the camei'a clutch. Door opening
and closing procedures, and the film loading opera¬
tions should be handled gently so that camera bore¬
sighting is not disturbed. A small microswitch as¬
sembly, that completes the circuit to the amber
light during camera operation, is preset to illuminate
the light when 0 to 15 feet of unexposed film remains
in the magazine. If the camera door is opened before
the film reaches the preset film-remaining value,
the microswitch assembly will reset to the starting
position. Hence, the door should not be opened after
the film has been advanced unless the magazine is
to be removed entirely.

The green light, adjacent to the amber film-remain¬
ing light, illuminates to indicate power continuity in
the camera circuits when the pilot places the power
switch ON. The green camera power light receives
power from the 28/14 volt ac bus and is controlled
by the DIM/BRIGHT rheostat control knob. This
light does not indicate the motor is actually running;
however, by touching the camera case as power is
applied, the pilot may be able to detect motor vibra¬
tions.

CAMERA CONTROL PANEL

Power Switch

The direct recording system control (DRSC) panel
contains the circuits to coordinate camera and fire
control system operation. Placing the rotary power
switch to ON energizes the following functions: the
camera motor, links the correlator light functions
to those of the radar and armament system; synchro¬
nize camera operation with antenna scan; and power
the camera clutch. With the power switch ON the
green light on the camera must illuminate indicating
power continuity exists between the control panel
and the camera motor. The green light does not,
however, indicate that the motor is running. The
camera will not operate unless the radar is on and
operating.

Witness Mark Switch

The witness mark switch may be used by the pilot to
mark a specific area on the film, i.e., to reference
a second target run, etc. The ON position of the
switch illuminates correlator light No, 7 continually.
The MC (momentary contact) position energizes a
single flash illumination. Since the No. 7 light is on
steadily during radar expanded sweep operation
(F-4C/D) and when AIM-7D/E missile is gone (F-4E),
it may be difficult to determine the difference between
expanded sweep (missile gone) and the ON function of
the switch when viewing the film. Hence, the MC
position provides the most feasible function.

Acquisition Rate Selector

The acquisition rate selector knob is a five position
knob which is used to select the desired film speed
from 2 to 6 frames per second (FPS) when operating
in a lock-on, track, boresight or BIT 2, 3, 5 or 6.

As the film speed is selected, the correct aperture
setting (f/stop) may be read on the opposite side of
the control. The f/stop value is for reference only
since the aperture is preset during ground operations.
The optimum FPS setting is 4 and the optimum f/stop
(as set on the ground) is 2.7.

BIT Switch (F-4E Only)

This switch is used by the ground crew for testing
the camera operation and the seven correlator lights.

AIM-4D TRAINING MISSILE

The AIM-4D training missile is a captive training
device used to train the aircrew in the use of the
AIM-4D missile, in target tone detection, and in
tactics. The preflight and inflight switch positions
of the live missile and the training missile are the
same. The training missile can be suspended from
any one of the AIM-4D missile launchers. The igni¬
ter cable is connected.

The training missile consists of a modified AIM-4D
guidance unit, a close-cycle cryogenic cooler, and
a six-channel event recorder. During a single pass
the following events are recorded (1) IR seeker

1-252

T.O. 1F-4C-34-1-1

CAMERA AND PERISCOPE ASSEMBLY

A. MOTOR POWER LIGHT (GREEN)

B. FILM REMAINING LIGHT (AMBER)

C. CAMERA DOOR

1. PERISCOPE ASSEMBLY

2. BEAM SPLITTER (POLARIZED)

3. RADAR INDICATOR

4. CAMERA

5. MIRROR

6. INTERNAL POLARIZED FILTER

7. OUTER POLARIZED FILTER AND

LEVER CONTROL

F4-34-I-494

Figure 1-125

slaved to radar antenna (2) tone received (3) IR
seeker self-track (4) trigger pulled, and (5) simu¬
lated motor ignition. (The sixth channel is a spare.)
Up to 20 minutes can be recorded.

During preflight the recorder, located aft of the
missile stabilizers, should be checked to determine
that a cartridge of paper is installed. The inflight
procedures and tone indications are the same as the
AIM-4D missile. For this reason, separate check¬
list procedures are not provided for die training
missile. The training missile is recycled automati¬
cally when the trigger is pulled or by depressing the
ARR button 2 minutes after the pass is initiated. The
events are recorded on a paper cartridge and de¬
veloped by exposure to sunlight or fluorescant light
for several minutes.

WARNING

To prevent inadvertent firing of a live mis¬
sile, a mixed load of live and training mis¬
siles should not be carried.

TDU-ll/B TARGET ROCKET
(5-INCH HVAR)

The TDU-ll/B target rocket (figure 1-127) is a mod¬
ified 5-inch HVAR (High Velocity Aircraft Rocket).
Four tracking flares have been added to the rocket
tail fins to increase the emitted infrared energy to
produce a stronger target for the AIM-9B Sidewinder
missile. The rocket is carried and fired from the
same launcher as the AIM-9B missile - the LAU-7/A
launcher. The firing signal is received through an
electrical cable (rocket pigtail) that is plugged into
and taped to the LAU-7/A launcher.

The TDU-ll/B target rocket is selected and launched
in the same manner as the AIM-9B missile. The
target rockets and missiles should be loaded such
that the AIM-9B is selected automatically after the
target rocket is fired. This is accomplished if the
target rockets are loaded on the left wing station and
the AIM-9's are loaded on the right wing station.

If the target rocket should fail to leave the rail within
3 seconds after the trigger switch is pulled, the tar¬
get rocket and the next AIM-9B missile should be
stepped over to prepare for the firing of the second

1-253

T.O. 1F-4C-34-1-1

12 3 4

Light 1 - Indicates Al radar is in heavy clutter operation.

Light 2 - Indicates Al Is armed and that the trigger switch is
depressed.

Light 3 - Indicates hold altitude light is on.

Light 4 - With the light on:

(a) With acquisition symbol on scope -- R1 or R2 was
selected.

(b) Without the acquisition symbol on scope - R4 was
selected.

With the light off:

(a) With acquisition symbol on scope - R3 was selected.

(b) Without acquisition symbol on scope -- R5 was selected.

Light 5 - Indicates AIM-7D/E missile gone.

Light 6 - Not used (IR system).

Light 7 - Indicates expanded sweep operation or that the Witness MK
switch is ON.

7 6 5

Light 1 - With light on:

Indicates R6 range if light 4 is on and R5 range if light 4 is
off.

With light off:

Indicates R4 range if lights 3 and 4 are off.

Light 2 - With light on:

Indicates Al is armed and trigger switch is depressed.

With light off:

Indicates Al is not armed and trigger switch is not depressed.

Light 3 - With light on:

Indicates R1 range if light 4 is on and R3 range if light 4 is
off.

With light off:

Indicates R4 range if lights 1 and 4 are off.

Light 4 - With light on:

Indicates R1 range if light 3 is on, R6 range if light 1 is on,
and R2 range if lights 1 and 3 are off.

With light off:

Indicates R4 range if lights 1 and 3 are off.

Light 5 - With light on:

Indicates radar is in special mode (TRACK).

With light off:

Indicates radar Is not In special mode (TRACK).

Light 6 - With light on:

Indicates radar set Is in high PRF operation.

With light off:

Indicates radar set is in low PRF operation.

Light 7 - With light on:

Indicates AIM-7D/E missile is gone or that witness mark
switch is ON.

With light off:

Indicates AIM-7D/E missile is not gone or that witness mark
switch is OFF.

F4-34-1-495

1-254

Figure 1-126

UNCLASS WED

T.O. 1F-4C-34-1-1

WEIGHT.215 POUNDS

LENGTH.6 FT., 3 IN.

DIAMETER.5 INCHES

FLIGHT LIMIT .Refer to T.O. 1F-4C-1

ROCKET HEAD.LEADFILLED MK6, MOD 1

4C-34- 1—1 —(128)

Figure 1-127

target rocket. This is accomplished by actuating the
missile selector switch to HEAT REJECT as neces¬
sary and observing the SW light on the missile con¬
trol panel.

TDD-22A/B TOW TARGET

The TDU-22A/B tow target is towed from the RMU-
8/A reel launcher. The target is capable of carrying
four flares. Flare ignition is accomplished by a
transmission from the UHF radio in the aircraft. For
TDU-22A/B target flare ignition procedures, refer
to section n, RMU-8/A tow target system. For an
illustration of the target, refer to T.O. 1F-4C-34-
1-1A.

TOW SYSTEM (RMU-8/A)

The tow system is a semi-automatic tow reel and
target launching mechanism designed for use in tar¬
get towing from high performance aircraft. The
system is capable of trailing a 20 to 240 pound target
on 40,000 feet of towline in approximately 8 minutes
after initiation of the launch sequence. The tow sys¬
tem consists of a ram air turbine powered reel-
launcher, control panels, towlines, and a target.

The reel-launcher is mounted on the centerline sta¬
tion of the aircraft. Operation of the reel-launcher
includes four operating cycles: launch, reel-out,
reel-in, and recovery. Each of the operating cycles
are outlined below along with flight recommendations*

LAUNCH

During launch, the target is lowered away from the
reel-launcher on a launching boom. The target sep¬
arates from the launcher and is reeled away from the
aircraft at about 300 feet per minute to a preset dis¬
tance of 200 feet The launcher then automatically
retracts to the reel. Target launch should be ini¬
tiated at 300 KCAS at an altitude of 15,000 to 20,000
feet in a straight-and-level attitude.

REEL-OUT

The reel-out operation begins when the launcher is
retracted. As the reel-out speed is increased to
4775 -5220feetper minute at an acceleration rate
of 2.1 feet per second, the AC may begin a climb to
mission altitude. A climb speed of 300 - 320 KCAS
or 0.8 Mach with a 0° bank is recommended. If nec¬
essary, a 15° maximum bank angle can be made. At
no time during reel-out should the cable tension ex¬
ceed 75 percent of the breaking tension for the length
of cable in transit. (Refer to T.O. 43E-17-1-101 for
flight restrictions of the cable.) The towline continues
to reel-out at a constant speed until a preset length
is reached. This is the out-stop setting. The towline
then decelerates at 2.1 feet per second and stops.

The target is then at tow length and intercepts may be
accomplished.

Mission altitude for towing should be 30,000 - 35,000
feet and should be planned so as not to require the

Change 5

1-255

T.O. 1F-4C-34-1-1

use of afterburner. An airspeed of 0.8 Mach (280 -
300 KCAS) and an angle of bank of 30° should not be
exceeded.

REEL-IN

After intercepts are completed, the reel-Ln cycle is
initiated. The power should be reduced to 80 percent
and a 250 KCAS descent maintained to a level off
altitude of 15,000 feet. During this descent, the
reel-in cycle can be initiated. During reel-in, the
15° bank and 300 KCAS limits should not be exceeded.
As the reel-in is initiated, the towline accelerates at
2.1 feet per second to a 3700 - 5000 feet per minute
reel-in rate. The 3700 feet per minute should be
maintained by increasing airspeed until the target
reaches a preset distance behind the tow aircraft, at
which time the towline decelerates at 2.1 feet per
second and stops 800 feet behind the aircraft.

Note

RMU-8/A REEL LAUNCHER

The RMU-8/A reel-launcher (figure 1-128) is housed
in a jettisonable, supersonic pod. Ground clearance
with target stowed is adequate to clear a tail hook
arresting cable with aircraft struts and tires flat.

If the launcher is down, however, the launcher will
not contact the runway even with normal tire and
strut inflation. The weight of the reel-luancher
(serviced), exclusive of towline weight, is 850
pounds. Installation of the RMU-8/A does not cause
any adverse flight characteristics; however, the AC
should expect to encounter the following phenomena;

1. Minor vibration during reeling operation,
particularly during reel acceleration and de¬
celeration.

2. High pitched whine (like a siren) during high
speed reeling.

3. Torque effect during high speed reeling.

Cable tension during reel-in should not exceed
a tension of 400 pounds less than the mission
tension.

RECOVERY

The launcher is down for launch and recovery only,
and is up during target tow. The reel contains a
nitrogen bottle to actuate the launcher and the pneu¬
matic brakes. It uses the aircraft emergency bus to
provide power for stopping the reel and cutting the
cable if aircraft power is lost.

During recovery operations, an altitude of 15,000
feet and an airspeed of 300 KCAS is recommended.

A straight-and-level attitude is desired although a
5° bank is allowed. As the TSO initiates the re¬
covery cycle, the launcher comes down and the target
is reeled in under manual control at about 800 feet
per minute. As the target approaches within 150 feet
(confirmed by chase plane), the cable speed must be
slowed down to a maximum speed of 150 feet per
minute. As target engages the launcher, the launcher
retracts and the target is clamped to the reel-
launcher.

When target has been shot off, cable recovery
is initiated as usual. When cable length
reaches 25 feet or when the cable starts whip¬
ping and balling (observed by secondary tow
plane or chase plane), the cable should be cut
immediately.

When the mission involves two tow planes, the sec¬
ondary tow plane flies in a position so that visual ref¬
erence of each reel operation is maintained. If the
primary tow plane receives verification that the tar¬
get has been shot off, cable recovery is initiated dur¬
ing a descent to 20,000 feet. Upon reaching the level
off altitude, the secondary tow plane assumes a posi¬
tion 500 feet abeam of the primary tow plane and
launches its target.

> CAUTION 1

Towline Length Sensing Unit

The towline length sensing unit contains pulsing
switches used in sensing the amount of towline reeled
out, three counter operated limit switches used in
automatic sequencing during the launch operations,
and a reset mechanism. The switches and switch
functions are listed below;

OUT STOP - The out stop switch is used to

set the maximum towline length
required (minus stopping dis¬
tance).

LAUNCH STOP - The launch stop switch deter¬
mines the point beyond which
high speed reel-out action is
permitted.

IN STOP

CABLE IN
OUT/OFF

- The in stop switch determines
the point at which deceleration
from high speed reel-in occurs,
within which high speed reel-in
may not be started, and within
which manually controlled tar¬
get recovery may be started.

- The cable switch is a three po¬
sition switch with positions of
IN, OUT, and OFF. This switch
allows the ground crew to simu¬
late a complete operating cycle.
For normal tow target operation,
the switch is positioned to OFF.

As the primary tow plane is initiating reel-in
procedures and the secondary tow plane is
launching, care should be taken to avoid cross¬
ing cables.

Blade Pitch Change Actuator

The blade pitch change actuator consists of a re¬
versible d-c motor and a switch package containing

1-256

T.O. 1F-4C-34-1-1

RMU-8/A REEL LAUNCHER

DRAG INDEX.6.4

LENGTH.160 inches

DIAMETER.20 inches

WEIGHT with tow cable and target .... approx. 1800 pounds
(Add 51 pounds for the Aero 27A Ejector Bomb Rack.)

F4-34-I-497

Figure 1-128 (Sheet 1 of 2)

1-257

T.O. 1F-4C-34-1-1

NITROGEN
,) PRESSURE
GAUGE

LAUNCH STOP

CABLE

UNLOCK

NITROGEN

SHUT-OFF

VALVE

CUTTER

ARMING SWITCH

SWITCH

VIEW THRU FORWARD
ACCESS DOOR

FORWARD
ACCESS DOOR

CABLE

CUTTER —.
CONNECTOR /

F4—34-1-497—2

TARGET LIMIT

_ AFT ACCESS
DOOR

TOWLINE LENGTH
SENSING UNIT

VIEW LOOKING
UP AND AFT

RMU-8/A REEL LAUNCHER

SADDLE SHEAVE

VIEW A-A

Figure 1-128 (Sheet 2 of 2)

1-258

T.O. 1F-4C-34-1-1

six limit switches. The d-c motor, through a gear
train, rotates the power unit blades clockwise during
recovery and counterclockwise during launching. The
six limit switches are cam operated and determine
the number of degrees rotation the blades turn and
the direction of the turn.

Speed Monitor Switch Assembly

The speed monitor switch assembly consists of four
switches. The operation of each switch is governed
by the power unit speed. The switches are set to
operate at 8600 to 9400 rpm (normal governing band),
at 9900 rpm (ten percent overspeed), and at 10,800
rpm (twenty percent overspeed). The 8600 and 9400
rpm switches perform target reel-out/reel-in speed
monitoring functions. The 9900 and 10,800 rpm
switches are for emergency control.

Central Control Box

The central control box contains function control re¬
lays and an acceleration monitor. The relays are
used to control the overall operation of the RMU-8/A.
The acceleration monitor is used to automatically
control change-rate of the towline speed during the
operating cycle.

Power Unit

The power unit consists of eight reversible-pitch
blades, each of which attaches to a central hub. The
reversible-pitch blades are arranged in two rows of
four blades each. The blade angle is controlled
through the blade pitch change actuator which is
mechanically coupled to the reversible-pitch blades
and drives the blades on their individual axis. The
power unit is driven by the wind force created by the
forward speed of the aircraft. The unit rotates coun¬
terclockwise (as viewed from the rear) during reel-
out and functions as a brake against the trailing tow-
line and target. The power unit rotates clockwise
(as viewed from the rear) during reel-in and func¬
tions as a turbine to furnish drive power to the trans¬
mission and spool during the recovery operation.

Tran smission Assembly

The transmission assembly couples the driving power
developed by the power unit through a gear train as¬
sembly to the capstan and through a slip-clutch mech¬
anism to the towline spool. The transmission assem¬
bly houses the gear train, clutches, oilpump, scaven¬
ger oil-pump, and the oil dip stick.

Clutch Mechanism

The clutch mechanism consists of two, over-running
sprag-type clutches and a constant torque slip-clutch’
driven through a gear train. The arrangement of the
clutch mechanism maintains towline tension between
the capstan and the towline spool to prevent towline
slippage on the capstans.

Spool and Levelwind

The spool and levelwind provides storage of the tow-
line which is reeled-out or reeled-in. For conve¬

nience in rewinding, the spool is removable. The
levelwind is driven by the spool and may be readily
disengaged for purposes of synchronization and
threading.

Lubrication

The lubrication system is a wet-sump type with auto¬
matic reversing, rotary, internal gear pumps located
in the transmission assembly. Positive lubrication
is furnished to the main drive gear mesh, capstan
bearing, clutch assembly, and power unit. A sepa¬
rate pump scavenges the power unit and discharges
the oil into the transmission assembly. The trans¬
mission assembly and clutch mechanism are capable
of operating approximately 10 seconds with an inter¬
rupted oil supply. During the target launch and re¬
covery operations, all oil is routed to the clutch as¬
sembly for cooling. There are also two oil pressure
switches, an oil pressure indicator, and a tempera¬
ture indicator in the system. The oil pressure
switches and the oil temperature indicator are safety
devices which provide a visual indication of low oil
pressure and excessive oil temperature to the opera¬
tor.

Pneumatic System

The pneumatic system provides the necessary power
to extend and retract the launcher and to apply the
brakes to the reel-launcher. A storage bottle con¬
tains compressed nitrogen at 3000 psi. The pressure
is reduced to 300 psi before it is delivered to any of
the operating mechanisms of the reel-launcher. This
supply of nitrogen permits approximately four com¬
plete operating cycles. When the storage bottle pres¬
sure drops below 700 psi, a light in the control panel
gives a low air indication. The latch that holds the
launcher in the retracted position is also operated by
nitrogen pressure. This latch is in series with the
actuating cylinder that forces the launcher down.

This is to assure that the latch is opened before the
launcher boom is extended. The pneumatic system is
designed so that towline tension is maintained at all
times during launcher extension and retraction and
so that the brakes are applied gradually to prevent
snapping of the towline. During an emergency the
brakes are applied instantly.

Launcher

A pneumatically operated target launcher is provided
to launch and retrieve the target through the region
of disturbed air flow around the RMU-8/A and the
airplane. The launcher also acts as a shock absorber
upon initial target contact during recovery. The
launcher contains two mechanical clamps which hold
the target when the launcher is fully retracted. These
automatically open as the launcher is lowered.

Towline Cutter

An explosive cartridge operated towline cutter is
mounted on the launcher support structure and pro¬
vides for cutting the towline under any possible flight
operating condition. The cutter is fired manually by
actuation of the emergency stop and towline cut switch

1-259

T.O. 1F-4C-34-1-1

SWITCH |

EMERG

PWR

FLARE

TONE

EMERG

STOP

RECOVER

TARGET

NORMAL

STOP

RMU-8/A CONTROL PAH ELS

F4-34-1-498

TOWUNE LENGTH

T TARGET

E 0UT

LAUNCHER

DOWN

WARNING

CUT TOWLlHt BEFORE EJECT IH6
IF AlHCRArT MUST 91
ABANDOHfD WITH TAMET OUT

CAUTION

DO HOT tH6HO UAUNCHtB
AT SPEEDS IH flCESS
OP 500 AIAS OH H«0.05

TOWLINE

CUT

STOP A CUT

LOW AIR LOW OIL

AUTO CUT
ARMEO

RECOVERY SPEED
INCREASE

OECREASE

LAUNCH

TARGET

Figure 1-129

and is automatically fired under certain emergency
conditions. The conditions under which the towline
is cut automatically are: a 20% overspeed (towline
reel rate of 6000 ft/min.) during any of the four op¬
erating cycles, or target approaching within 200 feet
of the aircraft after failure to slow down and stop af¬
ter passing through the preset in stop distance during
the reel-in cycle (towline cutter is actuated by an
anti-collision device).

Tension System

A strain gage bridge in the high tension sheave works
in conjunction with a regulated power supply to pre¬
sent an indication of towline tension on the towline
tension indicator.

Towline Speed Indicating System

A tachometer generator in the reel-launcher provides
an indication of towline speed to the operator and a
signal indicating the rate of change of speed to the
acceleration monitor.

CONTROLS AND INDICATORS

The control panels (figure 1-129) consist of two con¬
trol boxes which contain all controls and indicators
required to operate the system. These control panels
are located on the right console in the rear cockpit.
The control panels contain the following switches and
indicators.

1-260

T.O. 1F-4C-34-1-1

Towline Length Indicator

The towline length indicator indicates the distance
(in 10 foot increments) the target is from the reel-
launcher assembly.

Emergency Power Light

The EMERG PWR light provides an indication of
failure of the primary 28 volt d-c supply.

RMU-8/A Circuit Breaker

The 15 amp circuit breaker on the control panel
provides circuit overload protection for the RMU-
8/A.

Tow System Master Switch

The tow system master switch applies electrical
power to the system. The switch has two positions,
ON and OFF, and can be guarded to either position.

Target Out Light

The TARGET OUT light provides an indication that
the target has been launched or is loose in the
launcher because of lost towline tension.

Launcher Down Light

The LAUNCHER DOWN light provides an indication
that the target launcher assembly is in the down posi¬
tion or is not locked.

Towline Speed Indicator

The towline speed indicator provides an indication of
the speed the towline is entering or leaving the
RMU-8/A. The indicator is calibrated in feel-per-
minute and consists of two scales, a lower scale with
a range of 0 to 700 and an upper scale with a range
of 700 to 6500. The upper scale has a green arc to
indicate the normal operating range and a red line at
6000 feet-per-minute to indicate the maximum tur¬
bine speed. A green neon light on the dial indicates
which speed range is operative. The lower scale is
operative with the light off and the upper scale is
operative with the light on.

Towline Tension Indicator

The towline tension indicator provides an indication
of the tension of the towline. The indication presented
is calibrated in hundreds of pounds.

Auto Cut Armed Light

The AUTO CUT ARMED light provides the operator
with an indication that the anti-collision device is
armed. (Refer to Towline Cutter.)

Low Air Pressure Light

The LOW AIR PRESS light illuminates when the air
storage bottle is depleted to an air pressure of 700
psi or lower.

Low Oil Pressure Light

The LOW OIL PRESS light provides an indication of
an oil pressure of 2.0 psi or below during the launch
or recovery sequence, and of 40 psi or below during
the reel-out or reel-in sequence.

Hi Oil Temperature Light

The HI OIL TEMP light provides an indication of
high oil temperature should the oil reach a tempera¬
ture of 220“ (104° C).

Towline Cut Light

The TOWLINE CUT light functions in conjunction with
the stop and cut sequence. When the stop and cut se¬
quence is activated, the TOWLINE CUT light shows
that the action of cutting the towline has been accom¬
plished.

Reel-Out/Reel-ln Switch

The reel-out control provides for high speed deploy¬
ment of the tai’get. When reel-out is initiated with
the target stowed, the launch sequence is automati¬
cally completed first. The reel-in control provides
for high speed recovery of the target to within a short
distance from the aircraft. The switch has three po¬
sitions: REEL-OUT, REEL-IN and a spring-loaded
OFF position.

Flare Tone Control Button

The flare tone control button provides a means of
firing an IR flare remotely located in the target.

Emergency Stop and Towline Cut Switch

The emergency stop and towline cut switch provides
an emergency means of manually stopping and cut¬
ting the towline at any time. The switch has two po¬
sitions : STOP and CUT and a guarded OFF position.

Recovery Speed Switch

The recovery speed switch allows operating person¬
nel to control the speed at which the towline is re¬
covered during the final recovery period. The switch
has three positions, INCREASE, DECREASE and a
spring-loaded OFF position. Actuating the switch to
the INCREASE position incrementally increases the
blade angle of the power unit to increase the speed at
which the target is recovered, hi order to obtain a
large increase in recovery speed, the switch must be,
alternately actuated and released until a maximum
recovery speed of approximately 1000 feet per min¬
ute is achieved. Actuating the switch to the DE¬
CREASE position will continuously drive the power
unit blades toward the feather position and target
recovery speed will decrease. For small decreases
in target recovery speed, the switch must be actu¬
ated to the DECREASE position intermittently.

1-261

T.O. 1F-4C-34-1-1

CAUTION

If a recovery is made immediately following
launch (the blades will be at the reel-out
feather angle) the recovery speed switch must
first be actuated to the INCREASE position,
followed by actuation of the switch to the DE¬
CREASE position to drive the blades to the
reel-in feather angle.

is cycled to OFF and back ON. Ac power is provided
by one of the 115 volt single phase 400 cycle ac air¬
craft buses. The ac power is used by the acceleration
monitor. The electrical system is protected by three
circuit breakers: two 28 volt dc circuit breakers
(rated for 20 and 10 amperes) and a 115 volt ac cir¬
cuit breaker (rated for 5 amperes).

MODIFIED A/A 37U-15 TOW
TARGET SYSTEM

Launch Recover Switch

The launch/recover switch provides for the slow
speed launching of the target to a short distance be¬
hind the aircraft during the launch cycle and provides
for manual control of target recovery during the re¬
covery cycle. The launcher is extended during the
launch and recovery cycles. The switch has three
positions, LAUNCH TARGET, RECOVER TARGET,
and a spring-loaded OFF position. Momentary actu¬
ation of the switch to the LAUNCH TARGET or RE¬
COVER TARGET position is sufficient to initiate the
respective cycles.

Normal Stop Switch

The normal stop switch allows any operation that is in
progress to be halted. The switch has two positions,
NORMAL STOP and a spring-loaded OFF position.

Note

Modification of the A/A 37U-15 tow target
system provides a better target/runway
clearance during takeoff.

The A/A 37U-15 tow target system (figure 1-130)
consists of a tow reel pod, a tow reel, a boom and
launcher for installing the TDU-10/B or the modified
K-ll targets, and facilities for incorporating a para¬
chute recovery system for the target. The target
system is carried by a MAU-12B/A pylon and tow
target adapter on the left outboard wing station. The
tow system has the following functions: target launch,
cable reel-out, tow, and cable cut. Normal aircraft
conventional weapon controls are used for these func¬
tions.

BOOM AND LAUNCHER

Control Circuit Sequencing

The normal stop and the emergency stop and towline
cut functions can be initiated at all times. The nor¬
mal stop function must be initiated to interrupt any
cycle before initiating a new cycle. The following
table illustrates cycles that can be initiated after the
completion of a manual or automatic normal stop at
various towline lengths relative to the towline length
limit switch.

Target Position

Target Stowed

Target between stowed
position and in-stop
(2500 ft)

Target between in-stop
(2500 ft) and out-stop

Past out-stop

Functions Possible
Launch, Reel-Out
Reel-Out, Recover

Reel-Out, Reel-In

Reel-hi

The boom and launcher, attached to the side of the
adapter, provides mounting facilities for the tow tar¬
get. The boom and launcher holds the target until
launch. A nose guide channel holds the nose of the
target and keeps the target stable during flight.

PARACHUTE RECOVERY SYSTEM

A parachute recovery system may be used to recover
the tow target. The parachute and canister is attached
to the aft end of the pod by cloth tape. The cable is
attached to the parachute canister which, in turn, is
attached to a 15-foot length of nylon rope. The rope
is attached to a bridle loop cable on the tow target.
When cut, the falling cable drags behind the target
causing the parachute canister to tumble 180". The
canister reversal allows the wind pressure to move
aerodynamically operated levers which release the
canister lid. The lid acts as a drogue and deploys
the recovery parachute. Flight tests have been con¬
ducted without the parachute, in which case, the tar¬
get cannot be recovered after launch.

SYSTEM ELECTRICAL POWER

Primary dc electrical power for operation of the tow
system is provided by the aircraft 28 volt dc bus.
Emergency dc power is provided for by the aircraft
battery bus in case the primary dc power is lost.
During operation with emergency power, all normal
functioning of the system is automatically stopped
and all control switches are inoperative except the
emergency stop and towline cut switch. The system
will resume normal operation when normal aircraft
power is returned to the line and the master switch

TOW REEL

The tow reel, mounted in the center section of the tow
reel pod, is a one-way reel capable of carrying ap¬
proximately 2300 feet of 11/64 inch cable or 5000
feet of 1/8 inch cable. Cable reel-out speed is con¬
trolled by a self-energized inertial brake acting on
the one-way wheel drum. The brake is operated by
a centrifugal force built up in fly weights on the
drum. A duct admits ram air through the nose of the
pod to cool the tow reel braking unit.

1-262

T.O. 1F-4C-34-1-1

MODIFIED A/A 37U-15 TOW TARGET S/STEM

LAUNCHER

TDU-10B

TARGET

NOSE GUIDE
CHANNEL

TOW TARGET SYSTEM (COMPLETE):

DRAG NUMBER..

WEIGHT (Complete system with 1500 feet of 3/16 inch cable)
ADAPTER (With boom and launcher attached):

DRAG NUMBER.

WEIGHT.

LENGTH (Boom and Launcher).

(To be supplied)
988 Pounds

(To be supplied)
311 Pounds
11 Feet

TOW TARGET POD;

DRAG NUMBER.

WEIGHT (With 1500 feet of 3/16

WEIGHT OF CABLE.

LENGTH.

DIAMETER.

SUSPENSION LUG DISTANCE

(To be supplied)
482 Pounds
97.5 Pounds
13.4 Feet
18 Inches
14 Inches

TDU-10 B TOW TARGET

WEIGHT.

LENGTH.

WING SPAN . . . .

195 Pounds
16 Feet
5 Feet

FLIGHT LIMIT

if.' sss-i&s

T.O. 1F-4C-34-1-1

TDU-10/B TARGET

The TDU-10/B target consists of four fins or wings
mounted together to form a dart like shape. A bridle
cable loop and a 15-foot length of nylon rope form a
leader assembly between the tow cable and the target.
The bridle loop is attached to the target and the nylon
rope attaches to the reel cable and the bridle loop.

The rope provides dampening effect to the target dur¬
ing launch. While the target is stowed, the slack in
the bridle cable and nylon rope is lockwired and
taped to the target fins. This prevents the cable and
rope from whipping during flight and causing damage
to the target. When the target is launched, the lock-
wire and tape pull loose.

TOW TARGET OPERATION

Target Launch

I The AC launches the target by energizing the normal
release controls: select DIRECT, select BOMBS,

select the target station, and select master arm. The |
target is launched by depressing the bomb release
button once; cable reel-out follows at governed speed
to the available length. As the bomb button is re¬
leased, a rotary solenoid shifts a transfer switch to
enable the cutter circuits.

Target Release (Cable Cut)

Before revision K, which modified the tow system
jumper bundle, the squib operated cutter is energized
by depressing the bomb button a second time. After
revision K, the cutter is activated by placing the
arm nose/tail switch to the NOSE position. In either
configuration, an emergency (backup) cutter may be
activated by selecting the NOSE & TAIL or TAIL
position.

Note

The Checklist, and section II procedures of
this manual consider only the revision K
method of activating the cable cutter.

COMBAT SUPPORT EQUIPMENT

KB-18A STRIKE CAMERA SYSTEM

The F-4C/D/E aircraft can be equipped with the KB-
18A strike camera system after incorporation of the
following time compliance directives.

I F-4C - T.O. 1F-4C-603
F-4D - T.O. 1F-4D-525
F-4E - T.O. 1F-4E-516

The camera pod is installed in the left forward mis¬
sile well for F-4C aircraft modified by Mod 1778B.
T.O. 1F-4C-603 installs provisions for the KB-18
system in remaining aircraft in the right forward
missile well. F-4D/E aircraft are equipped for the
KB-18A camera pod in the right forward fuselage
missile well. The panoramic camera mounted in the
pod provides continuous film documentation of the
strike area throughout an air-to-ground armament
delivery. Camera operation is initiated by pressing
the trigger switch in the front cockpit or by pressing
the bomb button in either the front or rear cockpit.

An overrun dial on the camera control in the camera
pod is set before flight to provide extended camera
operation after the trigger switch or bomb button is
released. The AC may operate the camera without
expending munitions by pressing the extra picture
button on the KB-18A camera control panel in the
front cockpit (figure 1-131). The KB-18A strike
camera system includes the following components:

a. Camera and film magazine.

b. Camera control.

c. Temperature/defogging control system.

d. Remote camera power switch in the pod. (The
switch must be ON before flight.)

e. KB-18A camera control panel (front cockpit).

CAMERA AND FILM MAGAZINE

The camera has a 3-inch focal length (75mm), f/2.8
lens with automatic exposure control. Continuous
panoramic coverage is accomplished in the following

manner. A double dove prism is rotated in front of
the lens while the film is advanced across a narrow
slit at the focal plane of the camera. The film ad¬
vance is synchronized with prism rotation, project¬
ing the panoramic image on the film as the prism
scans a 180° front to rear, by 40" side to side area.
The automatic exposure control senses variations in
scene illumination and initiates compensatory apera-
ture adjustments, thereby enhancing dawn-to-dusk
photography. The film magazine is attached to the
camera body and accommodates 250 feet of 70mm
aerial roll film. The film is exposed at a pre-set
rate of 1, 2, or 4 frames per second and produces
photographs with a format size of 2.25 by 9.4 inches.

CAMERA CONTROL

The camera control in the pod contains switches and
electronic components necessary to ground test the
camera temperature control system and pre-select
camera operation. The adjustable controls on the
face panel include the cycle rate switch, overrun dial,
and automatic exposure index (AEI) switch. These
ground adjustments are established by mission re¬
quirements.

Overrun Dial

The overrun dial is set before flight and determines
the amount of time the camera operates after the
trigger switch or the bomb button is released. The
dial is calibrated in 2-second increments from 0 to
20 seconds and includes an additional 32-second dial
setting. The extra picture switch does not energize
the camera overrun circuit.

Cycle Rate Switch

The cycle rate switch is a three-position film speed
control. This switch enables selection of 1, 2, or 4
picture frames per second during camera operation.
The cycle rate switch is set in accordance with the
planned altitude/airspeed combination.

Change 6

1-264

T.O. 1F-4C-34-1-1

Figure 1-131

AEI Switch

The automatic exposure index switch enables selec¬
tion of four values of film exposure sensitivity.
These exposure index values are 40, 64, 80, or 100.

KB-18A Extra Picture Switch

The KB-18A camera control panel figure 1-131 is
mounted in the front cockpit near the flap control
panel. The panel contains the extra picture button
which allows the AC to operate the camera without
expending munitions. The camera operates at the
rate selected on the cycle rate switch when the extra
picture button is pressed.

Note

Before flight, the overrun dial, cycle rate
switch, AEI switch, and the power switch in
the camera pod must be properly set.

The camera operates automatically during air-to-
ground armament delivery. Furthermore, camera
operation continues until overrun time (set on the
overrun dial) terminates.

COMBAT DOCUMENTATION MOTION
PICTURE CAMERA SYSTEM

The combat documentation motion picture camera
system is provided on selected F-4C/D/E aircraft.
The camera system consists of two 16 mm motion
picture cameras; the N-9 forward looking and the
DBM-4 or KB-21 aft looking cameras. The cameras
are mounted in the aircraft as follows:

I a. (F-4C) Both the N-9 and DBM-4 are initially in¬
stalled in the chin dome. After T.O. 1F-4-820, the

N-9 camera is relocated to the recess well area of
door 137R.

b. (F-4D after T.O. 1F-4-820, and F-4E-45 and up)
The N-9 camera is installed within the recess area
of door 137R; the KB-21 is installed within door 137L.

The N-9 forward camera produces motion picture
film coverage of gunfire, rocket, and missile im¬
pacts. The DBM-4/KB-21 camera is oriented down
and aft to document bomb impacts and post strike
results of gunfire and rocket attacks. Normal sys¬
tem operation is controlled by actuation of the trigger
switch or bomb release button. Operation of the
cameras without the expenditure of ordnance is pro¬
vided by an extra picture button in the forward cock¬
pit (F-4C), or rear cockpit (F-4D/E). These are the
only cockpit controls associated with the cameras.
Each camera is equipped with a ground adjustable
timer to allow additional pictures to be taken after
release of the trigger switch or bomb button. The
aft looking camera has a delay timer to delay op¬
eration by a preset time.

F-4D/E aircraft have a quick release safety pin
which precludes camera ground operation. The pin
is installed in the outboard side of door 137R and
must be removed prior to flight.

N-9 AND DBM-4/KB-21 CAMERAS

The N-9 is a 16 mm motion picture camera which
uses standard 16 mm black and white or color film.
The camera is equipped with a variable focal length
(20-80 mm) lens and operates at camera speeds of
16, 32, or 64 frames per second. The film magazine
has a 100-foot capacity with daylight loading spools.
The top aft end of the magazine contains a window
through which the quantity of unexposed film is in¬
dicated.

The DBM-4 and KB-21 are 16 mm motion picture
cameras which use standard black and white or color
film. The cameras are equipped with a variable focal
length (17-68 mm) lens and a continuously variable
frame rate capability which is set by controls on the
cameras. The film magazine has a capacity of 200
feet.

SYSTEM CONTROLS

A relay panel under door 137R contains the camera
timers and other controls used for ground operations.
The camera power switch on the relay panel must be
ON to allow operation of the cameras. The camera
timers (one for each camera) are set to the desired
overrun time; i.e., the time desired for the cameras
to run after release of the trigger switch or bomb
button. A delay timer is provided for the aft looking
camera. When the mission involves guns or rockets,
it is desirable to start the aft looking camera at a
time later than firing time. The delay timer is set at
this desired time interval. Momentary actuation of
the bomb button or trigger switch activates the delay
timer and the overrun timers. The forward looking
camera begins running and continues until time-out
of the overrun timer. At the completion of the delay

Ch ang e 3

1-264A/(1-264B blank)

5i K

T.O. 1F-4C-34-1-1

time, the aft looking camera starts running and con¬
tinues for the duration of the aft looking camera over¬
run timer setting. If the bomb button is held pressed
for a period of time, the delay timer begins its
countdown when the button is first pressed but the
overrun timers begin counting down when the bomb
button is released. A second actuation of the bomb
button before the overrun timers have timed out
(cameras still running) recycles the overrun timers
so that the overrun time begins when the bomb button
is released the second time. The aft looking camera
delay timer is activated on the first actuation of the
bomb button and is not affected by a second actuation
unless the overrun sequence is completed. Each
timer has a setting range of approximately 1 to 30
seconds.

Note

Any actuation of the bomb button when the
landing gear is up causes the cameras to
operate regardless of other cockpit switch
configurations. The trigger switch, how¬
ever, will not operate the cameras unless
the missile/gun arm switches are armed.

Extra Picture Button

I The extra picture button is above the right console in
the forward cockpit (F-4C), and rear cockpit
(F-4D/E). The button operates the cameras any
time without the delivery of armament. Camera op¬
eration through the extra picture button is the same
as operation through the bomb button and trigger
switch. The overrun and delay timers function the
same as explained previously.

RADAR TRANSPONDER SST-181X

The radar X band transponder is installed in F-4C
aircraft after T.O. 1F-4C-577, in F-4D aircraft thru

block 33 with T.O. 1F-4D-510, and in F-4E aircraft
after T.O. 1F-4E-510. The transponder is used to
extend the range tracking capabilities of certain
ground-based tracking radar sets and to increase the
adverse weather navigation capabilities in underde¬
veloped areas. These are transportable navigation,
or special purpose X-band radars, which may be
moved to forward areas and used to vector the air¬
craft to any specific area of interest. The ground-
based radar transmitter emits X-band radar signals
which interrogate the SST-181X radar beacon in the
aircraft. The SST-181X, in turn, transmits a single
or double pulse reply (in the same frequency band) to
the interrogating radar set. Therefore, the radar
site is actually receiving a transmitted signal which
is considerably stronger than a radar echo. This
improves target acquisition capabilities at radar
maximum ranges, especially in adverse environ¬
mental conditions.

PULSE SELECTOR SWITCH

The pulse selector switch is on the rear cockpit right
console. The switch has positions of OFF (center),
SINGLE, and DOUBLE. If the pilot selects SINGLE,
a single reply pulse is generated for each interroga¬
tion. In DOUBLE, the system generates two reply

pulses at a predetermined spacing. The operating
mode (SINGLE or DOUBLE) may be determined dur¬
ing mission briefing or by direct voice communica¬
tion with the radar site.

RADAR TRANSPONDER OPERATION

There are no indicators that show system operation;
the pilot simply energizes the system by selecting
the single or double operating mode. Vectoring in¬
formation is obtained by voice communications be¬
tween the aircrew and the ground controller.

Change 3

1-265

T.O. 1F-4C-34-1-1

RELEASE

ASSEMBLY

INITIATOR
CABLE -

CTU-1/A RESUPPLY CONTAINER

DRAG INDEX.

WEIGHT EMPTY.

MAX. CONTAINER LOAD.

LENGTH.

DIAMETER.

F4-34-I-43!

Figure 1-132

CTU-l/A RESUPPLY CONTAINER

The CTU-l/A is a parachute retarded container used
to deliver combat supplies to ground forces (figure
1-132). The container may be loaded with any equip¬
ment up to a maximum weight of 500 lbs., provided
the equipment can be loaded to maintain the container
C.G. within allowable limits.

Note

The parachute system limits the delivery
speed to 450 KCAS maximum, and the de¬
livery altitude to 300 feet AGL minimum.

The CTU-l/A consists of three basic assemblies:
the fin stabilized container, an XM5 cartridge-actu¬
ated parachute release assembly, and the parachute
assembly. At release, the initiator cable attached
to the rack causes detonation of the cartridge-actu¬
ated release assembly. After a 0.3 second delay,
the release assembly ejects the tail cone and deploys

the pilot parachute. The pilot parachute in turn de¬
ploys the main parachute to a reefed diameter of 36
inches. Explosive cutters then part a reefing line
and initiate blossoming to full diameter. Container
descent is therefore controlled to an impact velocity
of approximately 30 feet per second and at a nearly
vertical impact angle.

CTU-l/A CENTER OF GRAVITY

At release, the aerodynamic stability of the loaded
container is specifically dependent on maintaining
the loaded container center of gravity within speci¬
fied limits. Improper C.G. control can result in
violently unstable separation characteristics. The
appropriate authority must therefore verify that the
weight and C.G. location are within allowable limits
as a function of the planned payload and release air¬
speed. A plot is provided in section IV, Supplemen¬
tary Data, so that the aircrew may establish the C.G.
required for a stable separation. CTU-l/A level de¬
livery bombing tables are provided in T.O. 1F-4C-
34-1-2.

1-266

T.O. 1F-4C-34-1-1

NORMAL AIRCREW PROCEVURES

TABLE OF CONTENTS

Introduction.* . . 2-1

Part 1. Normal Aircrew Procedures (F-4C) . 2-3
Part 2. Normal Aircrew Procedures (F-4D) . 2-27

Part 3. Normal Aircrew Procedures (F-4E) . 2-63

Part 4. Normal Aircrew Procedures

(F-4C/D/E).. 2-99

INTRODUCTION

In accordance with AFR 60-9, the aircrew is required
to use this checklist when operating this aircraft with
non-nuclear weapons. However, this checklist con¬
tains an exterior inspection of suspension equipment
and non-nuclear weapons (part 4 of this section) that
are considered mission essential which the aircrew
IS NOT REQUIRED TO PERFORM since the correct
installation and loading of suspension equipment and
non-nuclear weapons is the responsibility of certified
loading crew members. The exterior checks pre¬
ceded by a star (★) are considered SAFETY OF
FLIGHT ITEMS which should be checked by an air¬
crew member if time permits. The mission essential
exterior check may be performed if desired.

Note

During Delayed Flight or Alert, certain safe¬
ty pins may be removed, electrical cable
plugs may be connected, and missile motor
switches armed as directed by Major Com¬
mand or as directed by Local Commander
during combat conditions. Checklist items
assigned to be performed in the Arming
Area, may be performed in any Designated
area when the aircraft is on Delayed Flight
or Alert status.

The procedures contained in this section are repro¬
duced in checklist form and presented verbatim in
T.O. 1F-4C-34-1-1CL-1. Warnings, Cautions, Notes,
and Amplifications have not been included in the
checklist. When this section is changed or revised,
the checklist will be changed concurrently.

This section is divided into four parts according to
aircraft effectivity:

Part 1. F-4C Aircraft
Part 2. F-4D Aircraft
Part 3. F-4E Aircraft
Part 4. F-4C/D/E Aircraft

And each part is divided into the following categories:

a. (AC) Aircraft Commander System Checks, for¬
ward cockpit.

b. (P) Pilot or WSO (Weapon Systems Officer) Sys¬
tem Checks, rear cockpit. The term (P) is used
throughout this section.

c. Combat Weapons

d. Training Equipment

Each category is further divided according to weapon,
system, or equipment and is complete from preflight
through inflight. The format of this section follows
the format of the checklist which permits the aircrew
to reduce the size of his checklist by first removing
all parts that are not applicable to his aircraft, and
all checklists that do not apply to his crew duty. To
further reduce the size of the checklist, the aircrew
may remove all pages that do not apply to the squad¬
ron mission. Use the table of contents to assist in
determining the pages to be removed and filed for
possible future use, and the pages that will comprise
the usable checklist. Some pages in the checklist are
intentionally left blank to facilitate the removal of a
complete system or weapon category. Preflight
checks are illustrated in part 4 of this section.

Change 3

2-1/(2-2 blank)

T.O. 1F-4C-34-1-1

PART 1 NORMAL AIRCREW PROCEDURES

TABLE OF CONTENTS

(AC) SYSTEM CHECK

Optical Sight Check.

(PILOT) SYSTEM CHECK

Radar BIT (Refer to T.O. 1F-4C-
34-1-1A)

Radar Homing and Warning System
(Refer to T.O. 1F-4C-34-1-1A)

COMBAT WEAPONS

Bombs.

Dive and Level Bombing.

Emergency Bomb Release.

Loft Bombing.

Centerline Bomb Release (DCU-

94/A).

Post Strike.

Rockets.

CBU and Flare Dispensers.

A/B45Y-1, -2, -4 Spray Tank Dis¬

pensers . 2-7

TMU-28/B Spray Tank. 2-8

2-4 PAU-7/A Spray Tank. 2-8

SUU-16/A, -23/A Gun Pod ...... 2-9

AIM-7D/E/E-2, -9B/E Missiles
(Refer to T.O. 1F-4C-34-1-1 A)

AGM-12B/C/E Missiles. 2-9

AGM-45 Missiles

(Refer to T.O. 1F-4C-34-1-1 A)

TRAINING EQUIPMENT _

SUU-20 Bomb/Rocket Dispensers. ... 2-10 I

2-5 SUU-21/A Bomb Dispenser (DCU-94/A). 2-10A

2-5 SUU-21/A Bomb Dispenser (Modified). . 2-11

2-5 TDU-ll/B Target Rocket (5-inch

2-5 HVAR). 2-12

Modified A/A 37U-15 Tow Target Sys-

2-5 tern. 2-12

2-6 Inf light Procedures for Bombing Range

2-6 Selected Weapons. 2-13

2-6

Change 7

2-3

T.O. 1F-4C-34-1-1

Figure 2-1

OPTICAL SIGHT CHECK (F-4C)

1. Optical shade knob - OPEN

2. Reticle illumination - CHECK

a. Rotate illumination knob left/right and check
both filaments; use left (counterclockwise)
position during continuous operation.

b. Observe reticle image clearly focused.

c. Check 20, 40, and 60 mil references at 3,

6, 9, and 12 o'clock positions.

3. Observe date and depression calibration plac¬
ard. (On inside of reticle depression knob if
available.)

4. Align LOS along top of sight head (below ball
and race) and tangent to highest point of ra-
dome.

5. Rotate depression knob until 1/2 of pipper is
visible on combining glass (figure 2-1).

a. Depression knob should read within ± 2 mils
of step 3 placard. (With placard not avail¬
able depression knob should read approxi¬
mately 268 ± 2 mils.)

6. Reticle depression knob - 240 MILS I

a. Pick stationary point in LOS with top of
reticle.

b. Move bottom of reticle to stationary point
(60 mils travel); depression knob reads 180
mils.

c. Repeat steps a and b until sight zeros; de- I
pression knob reads ± 2 mils.

7. Reticle illumination - OFF

8. Optical shade knob - CLOSED

If further use of the sight is not anticipated,
close the shade to prevent sun light from en¬
tering optical system.

The sight is folded down by using the handle
(figure 2-1). Do not touch the sight reflector |
glass.

2-4

Change 7

T.O. 1F-4C-34-1-1

BOMBS [F-4C1

PREFLIGHT

| Refer to part 4, figures 2-20A and 2-21.

INFLIGHT

Note

After T.O. 1F-4-750 (BRU-5/A rack), the
following release procedures may be used
to release the M118 or MK 84 GP bomb from
the CL station. On unmodified aircraft the
DCU-94/A procedures may be used.

DIVE AND LEVEL BOMBING

1. Reticle depression knob - SET

2. Weapon selector knob - BOMBS

3. Arm nose tail switch - SET

4. Intrvl switch - SET (if applicable)

5. Station selector knob - LOADED STATION

6. Master arm switch - ARM

7. Bomb button - DEPRESS

EMERGENCY BOMB RELEASE

1. Weapon selector knob - BOMB/RIPPLE

2. Repeat above steps (3) thru (7), hold bomb
button depressed 4 seconds.

If all bombs do not release:

3. Weapon selector knob - RKTS & DISP

4. Weapon selector knob - BOMBS/RIPPLE

5. Bomb button - DEPRESS (hold 4 seconds)

LOFT BOMBING
Before Bomb Run

1. (P) Low angle knob - SET

2. (P) Pullup timer - SET

3. (P) Release timer - SET ZERO

4. Bomb mode selector knob - LOFT

5. Multiple weapons control panel - SET

a. Weapon selector knob - BOMBS/RIPPLE

b. Arm nose tail switch - NOSE & TAIL

c. Interval switch - SET

d. Station selector switch - SET

e. Master arm switch - SAFE

At IP

1. Bomb button - DEPRESS AND HOLD

The bomb button must be energized until the
final bomb is released.

2. At pullup point, throttles - FULL MIL POWER

At Release Point

Loft Bomb Delivery

Approach the IP at the preplanned altitude and true
airspeed. When over the IP, depress and hold the
bomb button energized until the final bomb is re¬
leased. When the bomb button is depressed, the
pullup light illuminates, the pullup timer starts, and
the ADI pointers center. One second prior to com¬
pletion of the pullup timer, the warning tone (motor
timer) is audible in the headset. This is the signal
to the AC to select full military power and begin
rotation into the pullup maneuver by flying the ADI
pointers. Upon completion of the pullup timer, the
pullup light goes out and the horizontal pointer begins
programming a 4-G pullup. When the aircraft atti¬
tude is at the preselected release angle, the pullup
light and the break light will illuminate. This is the
signal to the AC to immediately position the master
arm switch to ARM. Placing the master arm switch
to ARM initiates bomb release. After the final bomb
is released, the bomb button is released and the AC
initiates a wingover escape maneuver to achieve a
120° turn while diving toward minimum escape alti¬
tude. WTien the bomb button is released, the pullup
light and the break light goes out and the horizontal
pointer moves out of view.

After Escape Maneuver

1. Master arm switch - SAFE

2. Weapon selector knob - OFF

3. Bomb mode selector knob - OFF

Placing the bomb mode selector switch OFF,
removes power from the bombing timers.

CENTERLINE BOMB RELEASE (DCU-94/A)

Before Bomb Run

1. Bomb mode selector knob - DIRECT

2. Optical sight - SET (if required)

3. (P) Nuclear store consent switch - REL ARM

4. DCU-94/A CL stations select switch - FOR¬
WARD

5. Arm nose tail switch - ARM

Bomb Run

1. DCU-94/A master release lock switch -
FORWARD

a. CL Unlocked light - ON

2. Master arm switch - ARM

The master arm switch applies power to the
arm nose tail switch

3. Delivery maneuver - EXECUTE

If the DIRECT delivery mode is selected, the
bomb is released when the bomb button is
depressed.

1. Pullup light - ON

2. Master arm switch - ARM

Change 2

2-5

T.O. 1F-4C-34-1-1

Note

If the bomb does not release, recheck switch
positions, select the DIRECT release mode
and depress bomb button, or energize the
nuclear store jettison control.

POST STRIKE
Before Landing

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station selector switches (5)
AFT

4. Missile arm switch - SAFE

5. Missile power switch - OFF

6. Missile jett knob - OFF

Armament Area (De-arming)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

ROCKETS (F-4CI

PREFLIGHT

| Refer to part 4, figure 2-22.

INFLIGHT

ROCKET FIRING

1. Reticle depression - SET

2. Weapon selector knob - RKTS & DISP

3. Station selector knob - LOADED STATION

4. Master arm switch - ARM

5. Bomb button - DEPRESS

LAUNCHER RELEASE

1. Weapon selector knob - BOMBS/RIPPLE

2. Repeat above steps 3,4, and 5, hold bomb
button depressed 4 seconds.

If all launchers do not release:

3. Weapon selector knob - RKTS & DISP

4. Weapon selector knob - BOMBS/RIPPLE

5. Bomb button - DEPRESS (hold 4 seconds)

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station selector switches (5) -
AFT

4. Missile arm switch - SAFE

5. Missile power switch - OFF

6. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

CBU AND FLARE DISPENSERS (F-4C)

PREFLIGHT

| Refer to part 4, figure 2-23.

INFLIGHT

DISPENSING

1. Reticle depression knob - SET

2. Weapon selector knob - RKTS & DISP

a. (SUU-13, -38, -42) Weapon selector knob -
RKTS & DISP/SINGLE

3. (SUU-7) Intrvl - SET (if required)

4. Station selector knob - LOADED STATIONS

5. Master arm switches - ARM

6. Bomb button - DEPRESS (and hold if required)

7. (SUU-7) CBU lights - MONITOR

a. Blinking light - Tubes Remaining

b. CBU light ON steady - All tubes have re¬
ceived a firing pulse.

Note

The CBU lights monitor the SUU-7 dispenser
only.

DISPENSER RELEASE

1. Weapon selector knob - BOMBS/RIPPLE

2. Repeat above steps (4) thru (7), hold bomb but¬
ton depressed 4 seconds.

If all dispensers do not release:

3. Weapon selector knob - RKTS & DISP

4. Weapon selector knob - BOMBS/RIPPLE

5. Bomb button - DEPRESS (hold 4 seconds)

2-6

Change 1

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station selector switches (5) -
AFT

4. Missile arm switch - SAFE

T.O. 1F-4C-34-1-1

5. Missile power switch - OFF

6. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

A/B45Y-1, -2, -4 SPRAY TANK DISPENSERS (F-4C)

PREFLIGHT

| Refer to part 4, figure 2-24.

INFLIGHT

DISPENSING (A/B 45Y-1, -2, -4)

1. Weapon selector knob - RKTS & DISP

Note

The Weapon selector knob is positioned
RKTS & DISP/PAIRS to supply a release sig¬
nal to both outboard stations simultaneously.

If one tank is carried, it should be carried on
the left outboard station. Also, if it is desired
to operate only one tank (left side), the weapon
select knob must be positioned to RKTS &
DISP/SINGLE and the RESET switch must be
momentarily positioned to RESET before the
bomb release button is depressed again to
start dissemination. To disseminate from the
right wing station after the corresponding left
tank has been emptied, the weapon selector
knob may be positioned to RKTS & DISP/
PAIRS.

2. Station selector knob - LOADED STATIONS

3. Arm nose tail switch - NOSE & TAIL

4. Master arm switch - ARM

Note

Placing the master arm switch to ARM arms
the A/B 45Y-1 tank causing an explosive
squib to discharge, thereby pressurizing the
bladder of liquid.

Once the A/B 45Y-1 is armed, it cannot be
de-armed and therefore must not be brought
back to base.

Note

*On the A/B 45Y-2 dry agent spray tank, en¬
ergizing the master arm switch causes the
agent container to be pressurized by ram air
for proper dissemination. The Y-2 tank can
be de-armed by positioning the master arm
switch to SAFE.

*On the A/B 45Y-4 dry agent spray tank, en¬
ergizing the master arm switch arms the
tank. The Y-4 tank can be de-armed by po¬
sitioning the master arm switch to SAFE.

5. Bomb button - DEPRESSED

6. CBU light - MONITOR

a. Blinking light - spray remaining

b. CBU light on steady - no spray remaining

DISPENSER RELEASE

1. Wing tank jett switch - JETT

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station selector switches (5) -
AFT

4. Missile arm switch - SAFE

5. Missile power switch - OFF

6. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

Change 1

2-7

T.O. 1F-4C-34-1-1

TMU-28/B SPRAY TANK |F-4C)

PREFLIGHT

| Refer to part 4, figure 2-24.

INFLIGHT

1. Weapon selector knob - NOT IN RKTS & DISP

2. Arm nose tail switch - SAFE

3. Master arm switch - SAFE

DISPENSING

1. Station selector knob - OUTBD WING

2. Master arm switch - ARM

3. To extend boom, weapon selector knob - RKTS
& DISP/SINGLE

a. While boom is extending, CBU light(s) - ON
STEADY

b. Boom fully extended, CBU light(s) - BLINK¬
ING

4. To begin dispensing, bomb button - DEPRESS
AND HOLD (8 sec)

5. To stop dispensing, bomb button - RELEASE

6. Weapon selector knob - NOT IN RKTS & DISP

7. To retract boom, nose tail arm switch - NOSE
& TAIL

a. CBU light(s) will continue to blink after
boom is retracted.

The CBU light(s) will continue to blink until
power is removed from the aircraft, except
when the station selector knob is in OFF.
When the station selector knob is positioned
to OUTBD WING, the CBU lights will begin
blinking again.

8. Station selector knob - OFF
a. CBU lights - OFF

DISPENSER RELEASE

1. Wing tank jett switch - JETT

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station selector switches (5)
AFT

4. Missile arm switch - SAFE

5. Missile power switch - OFF

6. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

PAU-7/A SPRAY TANK |F-4C)

PREFLIGHT

| Refer to part 4, figure 2-24.

INFLIGHT

1. Weapon selector knob - NOT RKTS & DISP

2. Arm nose tail switch - SAFE

3. Master arm switch - SAFE

DISPENSING

1. Station selector knob - OUTBD WING

2. Weapon selector knob - RKTS & DISP/SINGLE

3. Master arm switch - ARM

4. To extend boom, arm nose tail switch - NOSE &
TAIL

5. To dispense, bomb button - DEPRESS AND
HOLD

Tank will dispense with boom up or down.

6. To stop dispensing, bomb button - RELEASE

7. To retract boom, nose tail arm switch - TAIL
(90 sec)

8. Station selector knob - OFF (after boom re
tract)

DISPENSER RELEASE

1. Wing tank jettison switch - JETT

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station selector switches (5)
AFT

4. Missile arm switch - SAFE

5. Missile power switch - OFF

6. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

2-8

Change 1

T.O. 1F-4C-34-1-1

SUU-16/A, -23/A GUN POD (F-4C)

PREFLIGHT

| Refer to part 4, figure 2-25.

INFLIGHT

STRAFING

1. Reticle depression knob - SET

2. Gun clear switch - NON-CLEAR or AUTO
CLEAR

3. Gun station selector switch - READY

4. Master arm switch - ARM, RAT OUT

5. Trigger switch - ACTUATE

FINAL BURST-SAFE GUNS (ROUNDS REMAINING)

1. Gun clear switch - AUTO CLEAR

2. Trigger switch - ACTUATE

I AGM-12B/C/E

PREFLIGHT

| Refer to part 4, figure 2-26.

INFLIGHT

TRANSMITTER CHECK

If required, perform a fly-by check as follows:

1. Gam-Aux switch - TEST

The transmitter timer is energized for 50 ±

10 seconds.

2. Control handle - TRANSMIT COMMANDS

BEFORE MISSILE LAUNCH

1. (AC, P) Oxygen diluter selector-100 PER¬
CENT

2. Weapon selector knob - GAM-83 (AGM-12)

3. Station selector knob - INBD or OUTBDWING

4. Launch pulse - POSITION
a. Step switch - RESET

Momentarily select RESET to direct the
first fire signal to the selected left wing
station.

MISSILE LAUNCH

Left Wing Station

1. Master arm switch - ARM

The arm position powers the station se¬
lector switch and completes the bomb button
intervalometer circuit.

3. Master arm switch - SAFE, RAT IN

4. Gun station selector switch - SAFE

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station selector switches (5) -
AFT

4. Missile arm switch - SAFE

5. Missile power switch - OFF

6. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

MISSILE [F-4C|

2. Bomb button - DEPRESS (2 sec. approx)

Depress and hold the bomb button until the
missile fires or until the launch is aborted
due to missile malfunction.

Note

After firing the first (left) missile, the fire
signal is automatically directed to the se¬
lected right wing station the next time the
bomb button is depressed.

Right Wing Station

If the first missile is to be launched from the right
wing station, and the left wing stations also contain
armament, proceed as follows:

1. Master arm switch - ARM

2. Station selector knob - OFF

Select the OFF position to safe the missile
launch circuit.

3. Gam-aux switch - INTERRUPT (hold)

Hold the momentary interrupt position until
after step 4 below.

Note

The AC can avoid transmitter output at this
time by doing one of two things: (1) Hold the
Gam-aux switch in INTERRUPT during step 4
below, or (2) position the weapon selector to
BOMBS SINGLE, then re-select GAM-83
after step 4.

Change 1

2-9

T.O. 1F-4C-34-1-1

4. Bomb button - DEPRESS MOMENTARILY

Momentarily depress the bomb button to set
the intervalometer so that the next fire signal
goes to the right station.

5. Gam-aux switch - RELEASE

6. Station selector knob - INBD or OUTBD WING
(LOADED STATIONS)

7. Bomb button - DEPRESS (2 sec. approx)

Depress and hold the bomb button until the
missile fires, or until the launch is aborted
due to missile malfunction.

Note

If the transmitter timer is energized during
step 4 above, step 7 should follow rapidly
thereafter so that the time cycle (50 ± 10 sec.)
is only slightly expired. Otherwise, the AC
may reset the timer by selecting GAM-AUX
INTERRUPT, and then selecting NORM as
the missile fires.

MISSILE FLIGHT (AGM-12E)

To prevent AGM-12E warhead from functioning:

1. Gam-aux switch - INTERRUPT (hold 4 sec.)

If it becomes necessary to safe the missile,
select Gam-aux INTERRUPT.

AFTER MISSILE ATTACK

1. Armament switches - OFF/SAFE

a. Master arm switch - SAFE

b. Station selector knob - OFF

2. Emergency vent handle - CYCLE

Pull to de-pressurize, then push to pressur¬
ize to cycle cockpit air in case of contamina¬
tion by missile exhaust gages.

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station selector switches (5) -
AFT.

4. Missile arm switch - SAFE

5. Missile power switch - OFF

6. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

3. AFTO Form 259 - COMPLETE

SUU-20 BOMB/ROCKET DISPENSERS (F-4C)

PREFLIGHT

Refer to part 4.

INFLIGHT

ROCKET DELIVERY

1. Optical sight - SET

2. Weapon selector knob - RKTS & DISP

3. Station selector knob - LOADED STATION

4. Intrvl switch - .10 or .14 ONLY

5. Master arm switch - ARM

6. Bomb button - DEPRESS

BOMB DELIVERY

1. Optical sight - SET

2. Weapon selector knob - BOMBS MODE
a. With one dispenser aboard - PAIRS

WARNING

If the SUU-20 containing both rockets and
bombs is aboard, and an empty TER is
aboard the opposite station (2 and 8), apply¬
ing the bomb release signal in a BOMBS
PAIRS mode may also launch a rocket. The
stepper circuits in the TER cause a feed¬
back pulse which may be of sufficient dura¬
tion to cause the rocket launch.

3. Intrvl switch - .10 or .14

4. Station selector knob - LOADED STATION

5. Master arm switch - ARM

6. Bomb button - DEPRESS

Not*

• There is no cockpit indication to determine
that all bombs or rockets have been re¬
leased or fired.

• The intervalometers within the SUU-20
can not be rehomed in flight for an at¬
tempt to release or fire a hung bomb or
rocket.

• Do not use an aircraft interval setting of
0.06.

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station selector switches (5)
AFT

4. Missile arm switch - SAFE

5. Missile power switch - OFF

6. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

2-10

Change 7

T.O. 1F-4C-34-1-1

SUU-21 /A BOMB DISPENSER DCU-94/A |F-4C|

PREFLIGHT

Refer to part 4, cockpit weapons check and Exterior
Inspection (SUU-21/A) -

INTERIOR INSPECTION (DCU-94/A)

Before applying external power:

1. All station selector switches (5) - AFT

2. Station select switch guard - INSTALLED

If other munitions are aboard, the required
guard should be installed.

3. Master release lock switch - AFT

4. Option selector knob - OFF

5. Bomb mode select knob - OFF

6. (P) Nuclear store consent switch - SAFE

With the dispenser doors open, proceed as follows:

7. External power - APPLY

8. Generator switches - EXT ON

9. Lamp test button - PRESS

a. Warn and unlocked lights - ON

10. Option selector knob - SAFE

a. Loaded station warn light(s) - FLASHING
(doors closing)

b. Loaded station warn light(s) - OFF (doors
closed)

11. Option selector knob - OFF

INFLIGHT

ON BOMB RANGE (DCU-94/A)

1. Option selector knob - SAFE

2. Loaded station select switch - FORWARD
a. Loaded station WARN light - ON

3. (P) Nuclear store consent switch - REL/ARM
a. Loaded station WARN light - OFF

4. Option selector knob - GRD

a. Loaded station WARN light - FLASHING
(doors opening)

b. Loaded station WARN light - ON (doors open)

5. Delivery mode selector knob - AS REQUIRED

6. Weapon selector knob - NOT RKTS & DISP

Note

When the SUU-21/A dispenser is loaded on
the inboard stations, bomb release will not
occur if the weapon selector knob is on RKTS
& DISP.

BEFORE BOMB RUN (DCU-94/A)

1. Master release lock switch - FORWARD
a. Loaded station UNLOCKED light - ON

2. Loaded station WARN light - ON

AFTER BOMB RELEASE (DCU-94/A)

Manual Operation

After each bomb release, the dispenser doors re¬
main open and additional switching procedures are

unnecessary. With DIRECT bombing mode selected,
the release system (pickle button) is hot. If it is
necessary to safe the system between runs, place the
master release lock switch AFT, and reselect FWD
just prior to the next run.

Automatic Operation

1. At bomb release, loaded station WARN light -
FLASHING

2. Loaded station WARN light - OFF (doors
closed)

3. Option selector knob - SAFE

4. Option selector knob - GRD

a. Loaded station WARN light - FLASHING

b. Loaded station WARN light - ON (doors open)

AFTER FINAL BOMB RELEASE (DCU-94/A)

1. (Auto mode) Loaded station WARN light -
FLASHING

2. (Auto mode) Loaded station WARN light - OFF
(doors closed)

3. Option selector knob - SAFE

a. (Man. mode) Loaded station WARN light -
FLASHING

b. (Man. mode) Loaded station WARN light -
OFF (doors closed)

4. Master release lock switch - AFT

a. Loaded station UNLOCKED light - OFF

5. Bomb mode selector knob - OFF

WARNING

If the dispenser doors do not close and all
bombs have not been expended, the aircraft
must be flown to avoid populated areas to the
greatest degree practicable.

AFTER LANDING (DCU-94/A)

To open dispenser doors, if required:

1. (P) Nuclear store consent switch - REL/ARM

2. Loaded station select switch - FORWARD

3. Option selector knob - GRD

a. Loaded station WARN light - FLASHING

b. Loaded station WARN light - ON (doors open)

4. All electrical power - REMOVED

Note

All electrical power must be removed from
the aircraft before performing steps 5, 6
and 7 to preclude the dispenser doors from
closing.

5. Option selector knob - OFF

6. All station select switches (5) - AFT

7. (P) Nuclear store consent switch - SAFE

2- 10A/(2-10B blank)

Change 7

T.O. 1F-4C-34-1-1

SUU-21/A BOMB DISPENSER MODIFIED |F-4C|

PREFLIGHT

Refer to part 4.

INTERIOR INSPECTION

If the dispenser doors are open, close the doors as
follows:

1. External power - APPLY

2. Generator switches - EXT ON

3. Armament safety override - DEPRESS

4. Station selector knob - INBD

5. Master arm switch - ARM

6. Arm nose tail switch - NOSE

a. Dispenser doors - CLOSE (Crew Chief Check)

7. Station select knob - OFF

8. Master arm switch - OFF

INFLIGHT

WEAPON RELEASE

1. Optical sight - SET

2. Weapon selector knob - BOMBS MODE
a. With one dispenser aboard - PAIRS

3. Station selector knob - INBD

4. Master arm switch - ARM

5. Arm nose tail switch - NOSE & TAIL

a. Dispenser doors - OPEN (Wingman Check)

6. Bomb button - DEPRESS

AFTER FINAL RELEASE

1. Arm nose tail switch - NOSE

a. Dispenser doors - CLOSE (Wingman Check)

2. Master arm switch - SAFE

3. Station selector knob - OFF

4. Sight mode selector knob - OFF

AFTER LANDING

To open SUU-21/A Dispenser Doors:

1. Armament safety override button - DEPRESS

2. Station selector knob - INBD

3. Master arm switch - ON

4. Arm nose tail switch - NOSE & TAIL
a. Dispenser door - OPEN

5. Station selector knob - OFF

6. Master arm switch - SAFE

Change 7

2-11

T.O. 1F-4C-34-1-1

TDU-11/B TARGET ROCKET (5-INCH HVAR) (F-4C)

PREFLIGHT

| Refer to figure 2-30.

INFLIGHT

To fire the target rocket, perform the following
procedures:

1. Optical sight - SET AS DESIRED

2. Missile select switch - HEAT

3. Applicable SW light - ON

If the SW light indicates that the station con¬
taining the target rocket is not selected,
actuate the missile select switch to HEAT
REJECT until the desired station is selected.

4. Missile arm switch - ARM
a. READY light - ON

5. Trigger switch - ACTUATE

After the target rocket is fired, maneuver
aircraft to pursue the target rocket, monitor

the aural tone in the headset, and prepare to
launch the AIM-9 missile at the target
rocket. Prior to launching the AIM-9 mis¬
sile, observe proper SW and READY light
indications, aircraft to target range, and
proper tone indication.

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station selector switches (5) -
AFT

4. Missile arm switch - SAFE

5. Missile power switch - OFF

6. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

MODIFIED A/A 37U-15 TOW TARGET SYSTEM (F-4C)

PREFLIGHT takeoff

| Refer to part 4, figure 2-29. Initiate a slow pitch rotation at 140 KIAS to obtain 8°

pitch attitude indicated on the ADI for lift-off at 180

ikiEl irur t0 190 KIAS - Decrease thrust after gear and flap

INFLIGHT retraction to ensure that 275 KIAS is not exceeded.

PRE-TAKEOFF

To reduce rolling tendencies immediately after take¬
off, the following aileron trim positions are recom¬
mended. Trim settings are the same with or without
centerline tank.

a. Dart system on station 1, station 9 empty: 2.5
inches left aileron down (trim 2.5 seconds to right

of neutral), 1.5 inches right rudder (trim 1.5 seconds
to right of neutral).

b. Dart system or station 1, external fuel tank on
station 9: 3.5 inches right aileron down (trim 3.5
seconds to left of neutral), 1.0 inch left rudder (trim
1.0 second to left of neutral).

Note

The tow target system, carried on the left
outboard wing station, may induce 20° to
30° errors in the remote compass trans¬
mitter. Due to this effect, the DG mode on
the compass controller should be selected.

Note

Refer to T.O. 1F-4C-1 External Store Limi¬
tations for A/A 37U-15 tow target system
inflight limitations.

TARGET DEPLOYMENT

1. Weapon selector knob - BOMBS PAIRS or
BOMBS SINGLE

Bombs single may be selected if there is a
deployable store on the right outboard wing
station, in which case the reset switch must
be positioned to RESET every time prior to
pressing the bomb release button.

2. Station selector knob - OUTBD WING

3. Arm nose tail switch - SAFE

4. Step switch - RESET (if applicable)

5. Master arm switch - ARM

6. Bomb button - DEPRESS

Depressing the bomb button once will release
the target.

2-12

Change 1

T.O. 1F-4C-34-1-1

j^CAurioN 0

Do not attempt to deploy a damaged dart tar¬
get. Motion of the damaged target after
launch is unpredictable. Possible contact
with the aircraft could be hazardous.

7. Master arm switch - SAFE

CABLE CUT

1. Master arm switch - ARM

2. Step switch - RESET (if applicable)

If BOMBS - SINGLE is selected, the reset
switch must be positioned to RESET in order
to return the release signal to the left wing
station

3. Tow cable - CUT

a. (Before Rev. K) Bomb button - DEPRESS

b. (After Rev. K) Arm nose tail switch - NOSE

4. Chase plane, acknowledge cable cut.

Emergency Cut

1. Arm nose tail switch - NOSE & TAIL or TAIL

2. Chase plane, acknowledge cable cut

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. All DCU-94/A station select switches (5) -
AFT

4. Missile arm switch - SAFE

5. Missile power switch - OFF

6. Missile jett knob - OFF

LANDING WITH STOWED TARGET (DAMAGED OR
UNDAMAGED)

1. Flaps - 1/2

2. Angle of attack - 17 to 18 UNITS

(With wing tank use less than 17 units.)

INFLIGHT PROCEDURES FOR BOMBING
RANGE SELECTED WEAPONS (F-4C)

These procedures are included for easy inflight ref¬
erence to support typical bombing, rocket, and
strafe missions on the bomb range. Aircrews are
still required to use appropriate checklists for pre¬
flight and jettison operations. Only the numbered
items need be performed; sub-steps are added for
clarity.

INFLIGHT

| ROCKET LAUNCHERS AND SUU-20

1. Reticle depression knob - SET

2. Weapon selector knob - RKTS & DISP

3. Intrvl switch - .10 or .14 ONLY

4. Station selector knob - AS REQUIRED

5. Master arm switch - ARM

| BOMBS - SUU-20

1. Reticle depression knob - SET

2. Weapon selector knob - BOMBS

3. Intrvl switch - .10 or .14 ONLY

4. Station selector knob - AS REQUIRED

5. Master arm switch - ARM

BOMBS-SUU-21/A(DCU-94/A)

1. Reticle depression knob - SET

2. Delivery mode - SELECT

3. Weapon selector knob - BOMBS

4. Option selector knob - SAFE

5. Loaded station selector switch - FORWARD
a. WARN light - ON

6. Nuclear store consent switch - REL/ARM
a. WARN light - OFF

7. Option selector knob - GRD

a. WARN light - FLASH

b. WARN light - ON

8. Master release lock switch - FORWARD
a. UNLOCKED light - ON

Note

For automatic operation, open doors by re¬
peating steps 4 and 7.

After Final Release (DCU-94/A)

1. Option selector knob - SAFE
a. WARN light - FLASH/OFF

2. Master release lock switch - AFT
a. UNLOCKED light - OFF

3. Loaded station select switch - AFT

4. (WSO) Nuclear consent switch - SAFE

BOMBS, SUU-21/A (MODIFIED)

1. Reticle depression knob - SET

2. Weapon selector knob - BOMBS MODE

a. With one dispenser aboard - PAIRS

3. Station selector knob - INBD

4. Master arm switch - ARM

5. Arm nose tail switch - NOSE & TAIL

a. Dispenser doors - OPEN (Wingman Check)

After Final Release (SUU-21/A Modified)

1. Arm nose tail switch - NOSE

a. Dispener doors - CLOSE (Wingman Check)

2. Master arm switch - SAFE

3. Station selector knob - OFF

STRAFE SUU-16/A, 23/A

1. Reticle depression knob - SET

2. Gun clear switch - AS REQUIRED

3. Gun station select switch - RE.ADY

4. Master arm switch - ARM

RANGE DEPARTURE

1. Sight mode selector knob - OFF

2. Delivery mode selector knob - OFF

3. Master arm switch - SAFE

4. Station selector knob - OFF

Change 7

2-13/(2-14 blank)

T.O. 1F-4C-34-1-1

PART 2

NORMAL AIRCREW PROCEDURES

F-4D

TABLE OF CONTENTS

(AC) SYSTEM CHECK

Optical Sight Check. 2-27

Optical Sight Malfunction Indications . . 2-29

(PILOT) SYSTEM CHECK

WRCS BIT Check. 2-31

Radar BIT (Refer to T.O. 1F-4C-
34-1-1A)

Radar Homing and Warning System
(Refer to T.O. 1F-4C-34-1-1B)

COMBAT WEAPONS

Bombs. 2-32

Direct Delivery Mode. 2-32

Dive Toss/Dive Laydown. 2-33

Laydown. 2-33

Offset Bombing/Target Find .... 2-34

LABS/Offset Bomb/Tgt Find .... 2-35

Loft Bombing - Ripple Release . . . 2-36

Centerline Weapons Release (DCU-

94/A). 2-36

Post Strike. 2-37

Rockets. 2-37

CBU and Flare Dispensers. 2-38

Direct Delivery Mode. 2-38

Dive Laydown. 2-38

Laydown. 2-38

Offset Bombing/Target Find .... 2-38

Post Strike. 2-40

Spray Tank Dispensers A/B 45Y-1,

Y-2, Y-4. 2-40

TMU-28/B Spray Tank. 2-41

PAU-7/A Spray Tank. 2-42

SUU-16/A, -23/A Gun Pod. 2-42

AIM-4D, -7D/E/E-2, -9B/E Missiles
(Refer to T.O. 1F-4C-34-1-1A)

AGM-12B/C/E Missiles. 2-43

AGM-45 Missile (Refer to T.O. 1F-
4C-34-1-1A)

MK 1 Mod 0 Weapon (Refer to T.O.

1F-4C-34-1-1A)

TRAINING EQUIPMENT

SUU-20 Bomb/Rocket Dispensers. . . . 2-44

SUU-21/A Bomb Dispenser. 2-44 |

SUU-21A Bomb Dispenser (Modified) . . 2-45

TDU-ll/B Target Rocket (5-inch

HVAR). 2-46

Modified A/A 37U-15 Tow Target Sys¬
tem . 2-46

Inflight Procedures for Bombing Range
Selected Weapons. 2-47

OPTICAL SIGHT CHECK (F-4D)

During the following procedures, the AC has the op¬
tion of using the BIT masks or noting the position of
the pipper on the ground to determine the magnitude
of reticle movement. Prior to selecting BIT 1, the
AC should position his head to the right until one-half
of the reticle is removed by the BIT 1 mask. The
BIT 2 mask must be rotated forward to remove the
top half of the reticle prior to selecting BIT 2. Radar
power must be available at least 30 seconds prior to
performing the BIT 2 check. For proper BIT check,
a 10-Mil sight depression must be used.

To avoid gyro system damage and to get an
accurate BIT check, gunsight BIT checks
should be performed only when the aircraft
is stopped or in level unaccelerated flight.

Note

Some aircraft do not have BIT masks.

1. Sight mode selector knob - STBY (Remain for
30 sec.)

The sight mode switch should remain in STBY
for 30 seconds to provide warmup power prior
to selecting other modes; however, this will
not damage the set if not accomplished.

2. (P) Radar power - TEST or STBY

Radar power should remain OFF until the
aircraft is operating on internal power and
with engines running over 50% rpm minimum.

This prevents overheating of radar compo¬
nents.

3. Sight shutter lever - OPEN

4. Sight mode selector knob - CAGE

Reticle should appear on the combining glass.

5. Reticle intensity control - CHECK

Check that the reticle intensity can be con¬
trolled.

6. Reticle depression counter - SET 10 MILS

7. Sight mode selector knob - CAGE to A/G to

A/A

a. Pipper at RBL, note position of pipper.

b. Check ± 2 mils between modes

With the sight mode selector knob in
CAGE, note the position of the pipper on
the ground, then rotate the sight mode
selector knob from CAGE to A/G, and
then to A/A. There should not be more
than 2 mils difference between the three
positions. This is the radar boresight line
(RBL).

Change 7

2-27

T.O. 1F-4C-34-1-1

CAGE,

A/G and A/A

BIT 1 POSITION

BIT 2

Notes

a. 10 mils must be set into manual depression window
(or proper read-out of BIT tests functions.

b. Rear cockpit radar power switch must be out of
"Off" position for ot least 30 seconds.

F4D-34-II-201

Figure 2-7

Note

When the sight mode selector knob is posi¬
tioned to CAGED, A/A, A/G, it remains
caged to the radar boresight line regardless
of the reticle depression counter setting.

This is true only when the aircraft is on the
ground; when airborne, the sight functions
normally.

8. Sight mode selector knob - BIT 1

a. The reticle should jump 25 ± 4 mils horizon¬
tally to the left (figure 2-7).

b. The roll tabs should rotate 90° clockwise.

c. The range bar should indicate 4000 feet (3
o'clock position).

Note

Radar power must be available 30 seconds
prior to performing BIT 2.

9. Sight mode selector knob - BIT 2

a. The reticle should jump 25 ± 4 mils down
from the BIT 1 position (figure 2-7).

b. The range bar should indicate 6700 feet
(12:30 o'clock position).

c. Roll tabs should indicate level flight.

10. Sight mode selector knob - A/A

a. The pipper should return to the radar bore-
sight line.

Optical Sight/Radar Tie-In

11. (AC) All armament switches - OFF/SAFE
a. Station green/amber light - OFF

12. Armament safety override button - PUSH IN

WARNING

When the armament safety override button is
energized, the jettison circuit is placed in an
inflight configuration, regardless of the land¬
ing gear handle position. The panic button
will jettison all external stores. When the
armament safety override button is pushed
IN, the AC has a jettison capability during
takeoff while weight is on the gear.

13. (P) Radar range - R1

14. (P) Track switch - MANUAL

15. Radar Mode selector knob - MAP, RDR or BST

16. (P) Action switch HA, position gate at 2 NM
and depress to FA.

a. (AC) Range bar indicates 12, 000 ft. (3o'clock)

17. (AC-P) Rotate manual Vc knob to obtain 200
knots closure; range bar begins moving toward
5 o'clock (6000 ft.) position.

18. (AC) Weapon selector - GUNS

19. (AC-P) Master arm switch - ARM (at 6000 ft.)

a. Range bar jumps to 1 o'clock.

b. Reticle slowly depresses 4 to 5 mils.

c. Range continues decreasing. Inside 4000 ft.

(3 o'clock), the pipper rises 4 to 5 mils as
range approaches 1500 feet. Stop the range
bar at 1500 feet (V c knob zero closure).

20. (AC) Reticle cage (ARR) button - DEPRESS
AND HOLD

a. Pipper should move not more than one mil.

21. (P) Action switch - HA and RELEASE
a. Radar breaks lock^range bar - OFF

22. (AC) Reticle cage (ARR) button - RELEASE
a. Pipper should move no more than one mil.

23. (AC) Master arm switch - SAFE

24. (AC) Sight mode selector knob - STBY or CAGE

CAUTION

DAMMAM i

The sight should be caged for takeoff and for
landing. Select STBY or CAGE to prevent
damage to the mirror drive assy.

25. (AC) Shutter lever - CLOSE (if leaving the air¬
plane).

If further use of the sight is not anticipated,
close the shutter to prevent sun light from
entering opticle system.

2-28

Change 2

77S?/Hd7hB

BIT MODE

RETICLE

ELEVATION

RETICLE

AZIMUTH

RETICAL

MOTION

MALFUNCTION

Reticle goes to +10 mils
with -10 set in the man¬
ual depression control.

Reticle remains at RBL.

Reticle drives to bottom
of combining glass.

Reticle drives 35 mils
to top of the combining
glass.

Reticle drives down but
not to 25 mils.

OPTICAL SIGHT STATUS

The manual depression CDX is
functioning, but cannot be manually
adjusted. Sight is useless for
WRCS laydown, dive bombing, rock¬
ets, air-to-ground, and guns air
to ground.

Dive toss, dive laydown, missile
and guns air-to-air and offset
bombing modes are operational.

There is either no effect, or all
modes except WRCS laydown, mis¬
siles and guns air-to-air, and off¬
set bomb will be inoperative.

All modes are inoperative.

WRCS laydown may be affected.

Correct lead angles are not being
generated and lead computing oper¬
ation is in error.

Reticle remains at RBL.

The sight may remain at the RBL in
all modes. It is also possible that
the sight may not respond to drift
signals applied to dive laydown,
WRCS laydown, or dive toss. How¬
ever, lead computing operation is
unaffected.

BIT 1 and
BIT 2

Reticle travels to ex¬
treme left of combining
glass.

Lead computations are incorrect.

BIT 2

Reticle remains at RBL
in azimuth after being

25 mils to left in BIT 1.

BIT malfunction - should not affect
lead computing mode.

BIT 1 and
BIT 2

Reticle remains at RBL
in elevation and azimuth.

The reticle may remain fixed at the
RBL in all modes.

BIT 1 and
BIT 2

Jittery Reticle.

Open loop from tachometer. This
defect will be present in all modes
of operation.

F4D-34-II-209-1

Figure 2-8 (Sheet 1 of 2)

2-29

T.O. 1F-4C-34-1-1

OPTICAL SIGHT MALFUNCTION INDICATIONS (CONT.)

ITEM

BIT MODE

MALFUNCTION

OPTICAL SIGHT STATUS

RANGE

BAR

BIT 1 and

BIT 2

Range bar is in stow
position.

Analog bar will remain stowed in
all modes of operation and lead
computing operation will not be
possible.

BIT 1

Range bar is at 1500'
position.

BIT malfunction - the analog bar
should function properly in all op¬
erational modes. Ranging and lead
computation may be correct.

BIT 2

Range bar is at 1000'
or 4000' position.

BIT 1 and
BIT 2

Range bar keeps driving.

Open loop - no feedback voltage
from the follow-up pot. This defect
will be present in all modes of op¬
eration.

BIT I and
BIT 2

Range bar is jittery.

No tachometer feedback to stabilize
servo amplifier. This defect will be
present in all modes of operation.

BIT 1 and
BIT 2

Range bar sticks.

Probably a mechanical bind is pres¬
ent. No mode of operation will be
free of this defect.

ROLL

TABS

BIT 1

Roll TABs remain at
wings level.

BIT malfunction, the roll tabs may
or may not work in flight.

BIT 1 and
BIT 2

Roll tabs rotate con¬
tinuously.

Open loop - no feedback signal.

Roll loop will not function in any
mode of operation.

BIT 1 and
BIT 2

Jittery roll tabs.

No tachometer feedback. This de¬
fect will show up in all modes of
operation.

F 4D-34-II-209—2

Figure 2-8 (Sheet 2 of 2)

2-30

T.O. 1F-4C-34-1-1

WRCS BIT CHECK (F-4DI

1. Delivery mode selector knob - OFF

2. HSI mode switches - NAV COMP

3. (P) Weapon delivery panel switches - SET

a. Activate switch - NORMAL

b. Tgt find switch - NORMAL

c. Range switch - X100

F-4D-32 and up: and all others after T.O.
IF-4-702.

4. (P) Control panel counters - SET

a. Target distance N/S - N274

b. Target distance E/W - E114

c. Target alt range - 170

d. Drag coefficient - 2.00

e. Release advance - 900

f. Release range - 050

(Use 500 if step 3c is X10)

Note

A NO-GO indication will occur if the above
parameters are not used during BIT.

When the target alt range counter is set
greater than 000, do not energize the target
find nor offset bomb mode unless; the air¬
craft altitude is greater than the altitude set
in the target alt range counter, or the WRCS
BIT button is depressed while performing the
WRCS target find offset bomb BIT check (step
14).

5. (P) INS mode selector knob - ALIGN or NAV

6. (P) BDHI mode switch - NAV COMP

7. (P) Radar mode switch - MAP-PPI

8. (P) Radar range switch - R1

9. (P) Radar power - STBY

10. (P) BIT selector knob - LAYDOWN, PUSH and
HOLD

a. Freeze button - PUSH ON (after 5 sec)

b. Range indicator illuminates.

c. After 15 seconds - GO/NO-GO

11. (P) BIT selector knob - DIVE LAYDOWN,
PUSH and HOLD

a. Freeze button - PUSH ON (after 5 sec)

b. After 15 seconds - GO/NO-GO

12. (P) BIT selector knob - DIVE TOSS, PUSH and
HOLD.

a. Freeze button - PUSH ON (after 5 sec)

b. After 15 seconds - GO/NO-GO

13. (P) BIT selector knob - AGM-45, PUSH and
HOLD

a. BDHI and HSI miles counter - 7.6 ± 0.5 NM

b. Alt indicator illuminates.

c. After 5 seconds, freeze button - PUSH ON.

d. Miles counter begins to decrease.

e. Approach indicator should indicate a pullup
command (LOW).

f. After 10 seconds, approach indicator should
indicate a level command (CENTER).

g. After 5 seconds - GO/NO-GO

h. After 5 seconds, approach indicator should
indicate a dive command (HIGH).

14. (P) BIT selector knob - TGT FIND OFFSET
BOMB

a. (P) BIT button - PUSH AND HOLD

The BIT button must be held depressed
without interruption until completion of
step 14o.

Pcaution}

When the BIT button is depressed, the WRCS
computer receives an aircraft altitude input
that is higher than the target altitude inserted
in step 4c. Step 14a must be performed be¬
fore steps 14b and 14c to ensure the WRCS
computer does not receive an aircraft alti¬
tude input that is lower than the target alti¬
tude inserted in step 4c. This is necessary
to avoid possible damage to the WRCS
pitch servo.

b. (AC) Delivery mode selector knob - TGT
FIND or OFFSET BOMB (check aircraft
effectivity).

c. (AC) Armament safety override button -
PUSH IN (check aircraft effectivity).

WARNING

When the armament override button is ener¬
gized, the jettison circuit is placed in an in¬
flight configuration, regardless of the land¬
ing gear handle position. The panic button
will jettison all external stores. The arma¬
ment safety override button will pop out when
the landing gear handle is raised.

Note

Steps 14b and 14c are not required and should
not be performed in F-4D-32 and up; and all
others after T.O. 1F-4-702.

d. (P) Along track cursor control - MOVE
(After 5 sec).

Move the along track cursor control first
in a forward direction to cause the along
track cursor to appear and move well up
on the scope before stopping it by releas¬
ing the cursor control. Improper operation
of the along track cursor control can cause
the WRCS computer to function as though
the RIP were behind the aircraft; i.e., the
cross track cursor responds in a reverse
direction to that normally obtained when the
cross track cursor control is operated.

Change 3

2-31

T.O. 1F-4C-34-1-1

e. (WSO) Cross track cursor - MOVE

Outboard movement of the cross track cur¬
sor control causes the cursor to move to
the right.

f. (WSO) Reset button - PUSH

g. (WSO) Cursors should return to center cross
track and zero range.

h. (WSO) Target insert button - PUSH ON

i. (WSO) Along track cursor; 6.5 miles on 0°
grid line (± 2000 feet). Cross track cursor;
right 30° (t 1.5°).

j. HSI bearing pointer should read 23°

± 2.5° to the right of the lubber line and the
TGT mode light on the HSI illuminates.

k. (WSO) BDHI No. 1 needle should read 23° ±
2.5° to the right of the top index.

l. (AC-WSO) HSI and BDHI miles counters
should read 4.8 ± 1.0 NM.

m. ADI vertical pointer should deflect full
right of center.

n. (WSO) Freeze button - PUSH ON

Miles counter decreases to zero, then in¬
creases. The sight roll tabs rotate as the
HSI miles counter passes through zero.

o. (WSO) After 15 seconds - GO/NO-GO

15. (WSO) WRCS control panel counters - RESET

a. Target distance N/S - N243

b. Target distance E/W - E/W Zero

c. Target alt range - 243

16. (WSO) Radar Power - TEST

17. (WSO) Test Switch - TEST 1

18. (WSO) WRCS BIT button - PUSH and HOLD

a. (WSO) Reset button - PUSH

b. (WSO) Target insert button - PUSH ON

c. (WSO) Along track cursor; 5.0 miles, checked
against the 5th BIT target. The near
edges of each should exactly coincide. Radar
receiver gain must be reduced to observe
the along track cursor.

d. (AC, WSO) Crosstrack cursor; zero azimuth
(t 1.5°). Note the actual position of the azi¬
muth cursor for in-flight evaluation of air¬
craft steering indicators (BDHI - HSI - ADI).

e. HSI bearing pointer should read under air¬
craft lubber line (± 2.5°), sight roll tabs
level, and ADI vertical pointer centered.

f (WSO) BDHI No. 1 needle under lubber line
(t 2.5°).

19. Delivery mode selector knob - OFF (check
aircraft effectivity)

This step is performed only if steps 14b and
14c are performed.

20. (WSO) WRCS BIT selector knob - RELEASE and
OFF

Release the BIT button and position the BIT
selector knob to OFF.

21. (WSO) Target alt range counter - SET 000

Note

• The B-sweep may not be centered on the
scope because of erroneous drift inputs to
the radar MAP-PPI and A/G mode when
performing this BIT check on the ground.

• If aircraft power is interrupted or fluctuates
during a BIT check, a NO-GO indication may
result and the BIT check should be repeated.

• If a momentary NO-GO is indicated as the
BIT button is released, disregard indication
if a GO was obtained with the button de¬
pressed.

22. (WSO) Weapon delivery panel - CHECK

a. Target find switch - NORM

b. Range switch - NORM

23. (WSO) Radar power - AS REQUIRED

BOMBS (F-4D)

PREFLIGHT

Refer to part 4.

INFLIGHT

Note

After T.O. 1F-4-750 (BRU-5/A rack), the
following release procedures may be used to
release the Ml 18 or MK 84 GP bomb from
the CL station. On unmodified aircraft, the
DCU-94/A procedures may be used.

DIRECT DELIVERY MODE

Bomb Release-Armed

1. Delivery mode selector knob - DIRECT

2. Sight mode selector knob - A/G

3. Reticle depression knob - SET

4. Weapon selector knob - BOMBS

5. Arm nose tail switch - SET

6. Intrvl switch - SET (if applicable)

7. Station select - LOADED STATION
a. Green light(s) - ON

8. Master arm switch - ARM
a. Amber light(s) - ON

9. Bomb button - DEPRESS

a. Pullup light - ON

b. When station is empty, amber light - OFF

Emergency Bomb Release

1. Weapon selector knob - BOMB/RIPPLE

2. Repeat above steps 5 through 9, hold bomb
button depressed 4 seconds.

If all bombs do not release:

3. Weapon selector knob - RKTS & DISP

4. Weapon selector knob - BOMB/RIPPLE

5. Bomb button - DEPRESS (hold 4 seconds)

2-32 Change 8

T.O. 1F-4C-34-1-1

DIVE TOSS/DIVE LAYDOWN
Before Bomb Run

1. Delivery mode selector knob - DIVE TOSS or
DIVE LAY

2. Sight mode selector knob - A/G

The sight reticle is electrically caged to the
radar boresight line and is drift stabilized.

3. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

4. (P) INS mode selector knob - NAV

5. (P) Radar mode selector knob - AIR-GND

6. (P) Radar range - R1

7. (P) Radar power - OPR

B-sweep, acquisition symbol, and el strobe
centered on scope.

8. (P) Antenna stab switch - NOR

9. (P) WRCS drag coefficient counter - SET (Dive
Toss Only)

10. (P) WRCS release range counter - SET (Dive
Lay Only)

a. Range switch - NORM or X100

Note

The position of the range switch will affect
the value placed in the release RANGE read¬
out: times 10 (NORMAL), or times 100.
(F-4D-32 and up; and all others after T.O.
1F-4D-702.)

11. (P) WRCS release advance - SET (if required)

12. Weapon selector knob - BOMBS

13. Arm nose tail switch - SET

14. Intrvl switch - SET (if required)

Note

The optical sight and the radar antenna is
drift stabilized. Additional upwind correc¬
tion must be made for the wind effect on the
high drag bombs. Wind correction is not re¬
quired for the low drag bombs (M117, etc.).

15. Station selector button(s) - PUSH ON
a. Green light(s) - ON

16. Master arm switch - ARM
a. Amber light(s) - ON

Bomb Run

1. (P) Receiver gain - MINIMUM

2. (P) Lockon target (CALL)

3. Bomb release button - DEPRESS AND HOLD
a. After bomb release, pullup light - ON

b. After station is empty, amber light - OFF
During the initial dive toward the target
area, the pilot reduces the receiver gain
to obtain a single return, depress the ac¬
tion switch to Half Action, place the range
strobe in the center of the return, and then
depress the action switch to Full Action
and release. After lockon, the AC places
the pipper on target, depresses and holds
the bomb release button, and initiates the
desired delivery maneuver. After the
bomb is automatically released, the pullup
light will illuminate and will go out when
the bomb button is released. The amber
light will go out when the station is empty.

LAYDOWN
Before Bomb Run

1. Delivery mode selector knob - LAYDOWN

2. Sight mode selector knob - A/G

3. Reticle depression counter - SET (if required)

Set the IP-to-target sight setting.

4. HSI mode switches - NAV COMP

If the HSI steering information is to be used,

the NAV COMP position must be selected.

5. (P) INS mode selector knob - NAV

6. (P) WRCS target range counter - SET

Set the distance from IP to target.

7. (P) WRCS release range counter - SET
a. Range switch - NORM or X100

8. (P) WRCS release advance counter - SET (if
required)

9. Weapon selector knob - BOMBS

10. Arm nose tail switch - SET

11. Intrvl switch - SET (if required)

12. Station selector button(s) - PUSH ON
a. Green light - ON

13. Master arm switch - ARM
a. Amber light - ON

Bomb Run

Approach the target at the preplanned release altitude
and airspeed. When the aircraft is directly over the
IP, or when the pipper is on target, depress and hold
the bomb release button. Maintain a constant air¬
speed, altitude, and course until the bomb is auto¬
matically released. The pullup light will illuminate
to indicate bomb release and will go out when the
bomb button is released. Wind corrections for the
bomb must be applied prior to depressing the bomb
button.

1. Bomb release button - DEPRESS AND HOLD

a. At bomb release, pullup light - ON

b. When a station is empty, amber ready light-
OFF

Change 1

2-33

T.O. 1F-4C-34-1-1

OFFSET BOMBING/TARGET FIND

Before IP

1. Delivery mode selector knob - OFFSET BOMB
or TGT FIND

2. Sight mode selector knob - A/G

The optical sight reticle is electrically caged
to the RBL and to 0° in azimuth. The roll
tabs display aircraft attitude until target in¬
sert, then steering commands to the target.

3. Navigation mode selector knob - NAV COMP

4. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

5. (P) INS mode selector knob - NAV

6. (P) BDHI mode switch - NAV COMP

7. (P) Weapon delivery panel - SET

a. Activate switch - NORMAL

b. Tgt find switch - NORMAL

c. Range switch - AS REQUIRED

Note

The position of the range switch will affect
the value placed in the release RANGE read¬
out: times 10 (NORMAL), or times 100.

(F-4D-32 and up, and all others after T.O.
1F-4D-702.)

8. (P) WRCS input counters - SET

a. Target distance N/S - 100-ft. increments

b. Target distance E/W - 100-ft. increments

c. IP altitude MSL - 100-ft. increments

d. Release range - 10-ft. or 100-ft. increments
(Offset bomb)

e. Release advance - Milliseconds (Offset
bomb, if required)

9. Weapon selector knob - BOMBS (Offset bomb)

Note

The ADI will not provide steering if the
weapon selector knob is on AGM-45.

10. Arm nose tail switch - SET

11. Intrvl switch - SET (if required)

12. Station selector button(s) - PUSH ON
a. Green light - ON

13. Master arm switch - ARM
a. Amber light - ON

Bomb Run-Offset Radar IP

1. (P) Radar power - OPR

2. (P) Radar mode switch - MAP-PPI

3. (P) Antenna stab switch - NOR

4. (P) Cursor intensity - ADJUST

5. (P) Antenna elevation - ADJUST

6. (P) Scan switch - WIDE

7. (P) Radar range selector knob - Rl

8. (P) Operate the along track cursor to position
the range cursor over the RIP.

2-34 Change 1

9. (P) Operate the cross track cursor to position
the offset cursor over the RIP.

10. (P) Freeze button - PUSH ON

Note

• The along track cursor must be moved first
to initiate cursor control. Position the inter
section of the cursors over the RIP and then
push the freeze button ON: the cursors be¬
gin tracking the RIP. The cursors can be
moved to touch-up the intersection location
over the RIP after the Freeze button is
pushed on.

• Do not position the range cursor below zero
range. If the range cursor is moved below
zero range and then moved out over the IP,
the steering information will be in error by
180° even though the cursor responds nor¬
mally to along track cursor control move¬
ments.

11. (P) Target insert button - PUSH ON

The steering instruments display steering
commands when the target insert button is
pushed ON, and the cursor intersection will
position over the target location and track the
target. If the target is on the scope, set the
target elevation on the ALT RANGE counter
and touch-up the cursors over the target.

12. Bomb release button - DEPRESS AND HOLD

(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, amber light - OFF

When the aircraft is on course to the tar¬
get and at the preplanned release altitude
and airspeed, depress and hold the bomb
release button until the bomb is released,
as indicated by illumination of the pullup
light.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

Bomb Run-Visual IP Fly-Over

1. (P) When over IP, freeze button and target in¬
sert button - PUSH ON

When the aircraft is directly over the IP, the
freeze button and the target insert button are
pushed ON simultaneously. The steering in¬
struments supply steering commands to the
target, and the cursors will position over,
and start tracking the target. If the target is
visible on the scope, the pilot may touch-up
the cursors when the target elevation is set in
the ALT RANGE control.

T.O. 1F-4C-34-1-1

2. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, amber light - OFF

When the aircraft is on course to the tar¬
get and at the preplanned release altitude
and true airspeed, depress and hold the
bomb release button until bomb release
occurs, indicated by the illumination of
the pullup light.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

LABS/OFFSET BOMB/TGT FIND

After Takeoff

1. Delivery mode selector knob - OFFSET BOMB
or TGT FIND

2. (P) Target find switch - HOLD

Select HOLD on the weapon delivery panel.

3. Sight mode selector knob - A/G

The optical sight reticle is electrically caged
to the RBL and to 0° in azimuth. The roll
tabs display aircraft attitude until target in¬
sert, then steering commands to the target.

4. Navigation mode selector knob - NAV COMP

5. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

6. (P) INS mode selector knob - NAV

7. (P) BDHI mode switch - NAV COMP

8. (P) WRCS input counters - SET

a. Target distance N/S - 100-ft increments

b. Target distance E/W - 100-ft increments

c. IP altitude MSL - 100-ft increments

d. Release range - 10-ft or 100-ft increments
(Offset bomb)

e. Release range - LABS pullup range, 10-ft
or 100-ft increments

Note

The (XI00) factor is selected through the
range switch on the weapon delivery panel.

f. Release advance - Milliseconds (Offset
bomb, if required)

9. Weapon selector knob - BOMBS (Offset bomb)

Note

The ADI will not provide steering if the
weapon selector knob is on AGM-45.

10. Arm nose tail switch - SET

11. Intrvl switch - SET (if required)

12. Station selector button(s) - PUSH ON
a. Green light - ON

13. Master arm switch - ARM
a. Amber light - ON

14. (P) Dual timers - SET

a. Pullup timer - Tj

b. Release timer - Tg

15. (P) Release gyro - SET

a. Low angle (LOFT) - DEG

Before Bomb Run

1. (P) Radar power - OPR

2. (p) Radar mode switch - MAP-PPI

3. (P) Antenna stab switch - NOR

4. (P) Cursor intensity - ADJUST

5. (P) Antenna elevation - ADJUST

6. (P) Scan switch - WIDE

7. (P) Radar range selector knob - R1

Bomb Run-Offset Radar IP

1. (P) Operate the along track control to position
the range cursor over the RIP,

2. (P) Operate the Cross Track control to position
the offset cursor over the RIP.

3. (P) Freeze button - PUSH ON

Note

• The along track cursor must be moved first
to initiate cursor control. Position the inter¬
section of the cursors over the RIP and then
push the freeze button ON; the cursors be¬
gin tracking the RIP. The cursors can be
moved to touch-up the intersection location
over the RIP after the Freeze button is
pushed on.

4. (P) Target insert button - PUSH ON

5. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, amber light - OFF

When the aircraft is on course to the target
and at the preplanned release altitude and
airspeed, depress and hold the bomb re¬
lease button until the bomb is released, as
indicated by illumination of the pullup light.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

Change 1

2-35

T.O. 1F-4C-34-1-1

Bomb Run-Visual IP Fly-Over

1. (P) When over IP, freeze button and target in¬
sert button - PUSH ON

When the aircraft is directly over the IP, the
freeze button and the target insert button are
pushed ON simultaneously. The steering in¬
struments supply steering commands to the
target, and the cursor will position over,
and start tracking the target. If the target is
visible on the scope, the pilot may touch-up
the cursors when the target elevation is set in
the ALT RANGE control.

2. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, amber light - OFF

When the aircraft is on course to the tar¬
get and at the preplanned release altitude
and true airspeed, depress and hold the
bomb release button until bomb release oc¬
curs, indicated by the illumination of the
pullup light.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start in¬
creasing in value.

Bomb Run-LABS/TGT Find

1. Delivery mode selector (LABS) - AS REQUIRED

Select the planned delivery mode.

Note

With the TGT find switch on HOLD, the de¬
livery mode selector may be positioned to any
LABS mode without losing WRCS function.

2. (P) Along track and cross track controls -
AS REQUIRED (visual or radar IP)

3. (P) Freeze control - PUSH ON

4. (P) Target insert control - PUSH ON

5. (P) After target insert, activate switch - ON

Select the ON position only after steering
instruments have transitioned to target.

6. At warning tone (Tj start) - MIL POWER
PULLUP

7. Bomb button - DEPRESS AND HOLD

LOFT BOMBING-RIPPLE RELEASE
Before Bomb Run

1. (P) Activate switch - NORMAL

When the WRCS is not used with the LABS
modes, the target find switch and/or the acti¬
vate switch on the weapons delivery panel
must be positioned to NORMAL.

2. (P) Low angle knob - SET

3. (P) Pull up timer - SET

4. (P) Release timer - SET ZERO

5. Delivery mode selector knob - LOFT

6. Pedestal panel - SET

a. Weapon selector knob - BOMB/RIPPLE

b. Arm nose tail switch - NOSE & TAIL

c. Intrvl switch - SET

d. Station selector button(s) - PUSH ON
(1) Green light - ON

e. Master arm switch - ARM
(1) Amber light - ON

At IP

1. Bomb button - DEPRESS AND HOLD

The bomb button must be energized until the
final bomb is released.

2. At pullup point, throttles - FULL MIL POWER

LOFT BOMB DELIVERY

Approach the IP at the preplanned altitude and true
airspeed. When over the IP, depress and hold the
bomb button energized until the final bomb is released.
When the bomb button is depressed, the pullup light
will illuminate, the pullup timer will begin, and the
ADI pointers will center. Upon completion of the
pullup timer, the pullup light and the reticle light will
go out and the horizontal pointer will begin program¬
ming a 4-G pullup. This is the signal to the AC to
select full military power and begin rotation into the
pullup maneuver by flying the ADI pointers (4-G
pullup) or the accelerometer. Since the sight reticle
is pitch stabilized, it will not be in view above loft
angles of 20°. When the aircraft attitude is at the
preselected release angle, the pullup light and the
reticle light illuminates and the bombs will begin
releasing in a ripple sequence. After the final bomb
is released, the bomb button is released and the AC
initiates a wingover escape maneuver to achieve a
120° turn while diving toward minimum escape alti¬
tude. When the bomb button is released, the pullup
light will go out, and the horizontal pointer will move
out of view.

AFTER ESCAPE MANEUVER

1. Master arm switch - SAFE

2. Station selector buttons (5) - OFF

3. Delivery mode selector knob - OFF

Placing the delivery mode selector knob to
OFF removes power from the bombing tim¬
ers.

CENTERLINE WEAPON RELEASE (DCU-94/A)

(F-4D THRU BLK 33)

Before Bomb Run

1. Delivery mode selector knob - DIRECT or AS
REQUIRED

2. Optical sight - SET (if required)

3. (P) Nuclear store consent switch - REL/ARM

4. DCU-94/A CL station selector switch - FOR¬
WARD

5. Arm nose tail switch - ARM

2-36

Change 1

T.O, 1F-4C-34-1-1

Bomb Run

POST STRIKE

1. DCU-94/A master release lock switch - FOR¬
WARD

a. CL UNLOCKED light - ON

2. Master arm switch - ARM

The master arm switch allows power to the
arm nose tail switch.

3. Delivery maneuver - EXECUTE

If the DIRECT delivery mode is selected, the
bomb is released when the bomb button is
depressed.

Note

Before Landing

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. Gun & stores switch - NORMAL

4. Sight mode selector knob - STBY, or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

If the bomb does not release, recheck switch Armament Area (De-arming)

positions, select the DIRECT release mode

and depress bomb button, or energize the nu- 1. Armament switches - OFF or SAFE

clear store jettison control. 2. Aircrew - HANDS IN VIEW

PREFLIGHT

| Refer to part 4, figure 2-22.

INFLIGHT

ROCKET FIRING

If all launchers do not release:

4. Weapon selector knob - RKTS & DISP

5. Weapon selector knob - BOMBS/RIPPLE

6. Bomb button - DEPRESS (Hold 4 seconds)

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Weapon selector knob - RKTS & DISP/SINGLE

5. Station select - LOADED STATION
a. Green light - ON

6. Master arm switch - ARM
a. Amber light - ON

7. Bomb button - DEPRESS

LAUNCHER RELEASE

1. Delivery mode selector knob - DIRECT

2. Weapon selector knob - BOMBS/RIPPLE

3. Repeat above steps 5, 6, and 7, hold bomb
button depressed 4 sec.

a. When station is empty, amber light - OFF

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Gun & stores switch - NORMAL

4. Sight mode selector knob - STBY or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

Change 1

2-37

T.O. 1F-4C-34-1-1

CBU AND FLARE DISPENSERS (F-4D)

PREFLIGHT

| Refer to part 4, figure 2-23.

INFLIGHT

DIRECT DELIVERY MODE
Dispensing

1. Delivery mode selector knob - DIRECT

2. Sight mode selector knob - A/G

3. Reticle depression knob - SET

4. Weapon selector knob - RKTS & DISP

a. (SUU-13, -38, -42) Weapon selector knob -
RKTS & DISP/SINGLF.

5. (SUU-7) Intrvl switch - SET (if required)

6. Station select - LOADED STATIONS
a. Green light - ON

7. Master arm switch - ARM
a. Amber light - ON

8. Bomb button - DEPRESS AND HOLD

9. (SUU-7) CBU lights - MONITOR

a. Blinking light - Tubes Remaining

b. Amber light out - All tubes have received a
firing pulse.

Note

The CBU lights will not monitor the empty
status of the flare dispenser, SUU-13, SUU-
38, SUU-42.

Dispenser Release

1. Delivery mode selector knob - DIRECT

2. Weapon selector knob - BOMBS/RIPPLE

3. Repeat above steps 6 thru 9, hold bomb button
depressed 4 seconds.

If all dispensers do not release:

4. Weapon selector knob - RKTS & DISP

5. Weapon selector knob - BOMBS/RIPPLE

6. Bomb button - DEPRESS (Hold 4 seconds)

DIVE LAYDOWN
Before Bomb Run

1. Delivery mode selector knob - DIVE LAY

2. Sight mode selector knob - A/G

The sight reticle is electrically caged to the
radar boresight line and is drift stabilized.

3. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

4. (P) INS mode selector knob - NAV

5. (P) Radar mode selector knob - AIR-GND

6. (P) Radar range - R1

7. (P) Radar power - OPR

B-sweep, acquisition symbol, and el strobe

centered on scope.

2-38 Change 1

8. (P) Antenna stab switch - NOR

9. (P) WRCS release range counter - SET

Set the bomb range from release to impact.

10. (P) WRCS release advance - SET (if required)

11. (P) Range switch - NORM or X100

12. Weapon selector knob - RKTS & DISP

a. (SUU-13, -38, -42) Weapon selector knob -
RKTS & DISP/SINGLE

13. (SUU-7) Intrvl switch - SET (if required)

Note

The optical sight and the radar antenna is
drift stabilized. Upwind correction must be
made for the wind effect on the high drag
bombs. Wind correction is not required for
the low drag bombs (M117 GP, etc.).

14. Station selector button(s) - PUSH ON
a. Green light(s) - ON

15. Master arm switch - ARM
a. Amber light(s) - ON

Bomb Run

1. (P) Receiver gain - MINIMUM

2. (P) Lockon target

3. Bomb release button - DEPRESS AND HOLD

4. (SUU-7) CBU lights - MONITOR

a. Blinking light - Tubes remaining

b. Amber light out - All tubes have received a
firing pulse.

Note

• The CBU lights will not monitor the empty
status of the flare dispenser, SUU-13,

SUU-38.

• During the initial dive toward the target area,
the pilot reduces the receiver gain to obtain
a single return, depress the action switch to
Half-Action, place the range strobe in the
center of the return, and then depress the
action switch to Full-Action and release. Af¬
ter lockon, the AC places the pipper on tar¬
get, depresses and holds the bomb release
button, and initiates the desired delivery
maneuver. After the bomb is automatically
released, the pullup light will illuminate and
will go out when the bomb button is released.

LAYDOWN

Before Bomb Run

1. Delivery mode selector knob - LAYDOWN

2. Sight mode selector knob - A/G

3. Reticle depression counter - SET (if required)

Set the IP-to-target sight setting.

4. HSI mode switches - NAV COMP

If the HSI steering information is to be used,
the NAV COMP position must be selected.

T.O. 1F-4C-34-1-1

5. (P) INS mode selector knob - NAV

6. (P) WRCS target range counter - SET

Set the distance from IP to target.

7. (P) WRCS release range counter - SET

Set the bomb range from release to impact.

8. (P) WRCS release advance counter - SET (if

required)

9. Range switch - NORM or X100

10. Weapon selector knob - RKTS & DISP

a. (SUU-13, -38, -42) Weapon selector knob -
RKTS & DISP/SINGLE

11. (SUU-7) Intrvl switch - SET (if required)

12. Station selector button(s) - PUSH ON

a. Green light - ON

13. Master arm switch - ARM
a. Amber light - ON

Bomb Run

Approach the target at the preplanned release alti¬
tude and airspeed. When the aircraft is directly over
the IP, or when the pipper is on target, depress and
hold the bomb release button. Maintain a constant
airspeed, altitude, and course until the bomb is auto¬
matically released. The pullup light will illuminate
to indicate bomb release and will go out when the
bomb button is released. Wind corrections for the
bomb must be applied prior to depressing the bomb
button.

1. Bomb release button - DEPRESS AND HOLD

2. (SUU-7) CBU lights - MONITOR

a. Blinking light - Tubes Remaining

b. Amber light out - All tubes have received a
firing pulse.

Note

The CBU lights will not monitor the empty
status of the flare dispenser, SUU-13, SUU-
38, SUU-42.

OFFSET BOMBING/TARGET FIND
Before IP

1. Delivery mode selector knob - OFFSET BOMB
or TGT FIND

2. Sight mode selector knob - A/G

The optical sight reticle is electrically caged
to the RBL and to 0 C in azimuth. The roll tabs
display aircraft attitude until target insert,
then steering commands to the target.

3. Navigation mode selector knob - NAV COMP

4. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

5. (P) INS mode selector knob - NAV

6. (P) BDHI mode switch - NAV COMP

7. (P) Weapon delivery panel - SET

a. Activate switch - NORMAL

b. Tgt find switch - NORMAL

c. Range switch - AS REQUIRED

8. (P) WRCS input counters - SET

a. Target distance N/S - 100-ft increments

b. Target distance E/W - 100-ft increments

c. IP altitude MSL - 100-ft increments

d. Release range - 10-ft or 100-ft increments
(Offset bomb)

e. Release advance - Milliseconds (Offset
bomb, if required)

9. Weapon selector knob - RKTS & DISP (Offset
bomb)

a. (SUU-13, -38, -42) Weapon selector knob -
RKTS & DISP/SINGLE

10. (SUU-7) Intrvl switch - SET (if required)

Note

The ADI will not provide steering if the
weapon selector knob is on AGM-45.

11. Station selector button(s) - PUSH ON
a. Green light - ON

12. Master arm switch - ARM
a. Amber light - ON

Bomb Run-Offset Radar IP

1. (P) Radar power - OPR

2. (P) Radar mode switch - MAP-PPI

3. (P) Antenna stab switch - NOR

4. (P) Cursor intensity - ADJUST

5. (P) Antenna elevation - ADJUST

6. (P) Scan switch - WIDE

7. (P) Radar range selector knob - R1

8. (P) Operate the along track cursor to position
the range cursor over the RIP.

9. (P) Operate the cross track cursor to position
the offset cursor over the RIP.

10. (P) Freeze button - PUSH ON

Note

• The along track cursor must be moved first
to initiate cursor control. Position the inter¬
section of the cursors over the RIP and then
push the freeze button ON: the cursors begin
tracking the RIP. The cursors can be moved
to touch-up the intersection location over the
RIP after the Freeze button is pushed on.

* Do not position the range cursor below zero
range. If the range cursor is moved below
zero range and then moved out over the IP,
the steering information will be in error by
180 even though the cursor responds nor¬
mally to along track cursor control move¬
ments.

11. (P) Target insert button - PUSH ON

12. Bomb release button - DEPRESS AND HOLD
(Offset Bomb)

Change 1

2-39

T.O. 1F-4C-34-1-1

13. (SUU-7) CBU lights - MONITOR

a. Blinking light - Tubes Remaining

b. Amber light out - All tubes have received a
firing pulse.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

Note

The CBU lights will not monitor the empty
status of the flare dispenser, SUU-13, SUU-
38, SUU-42.

Bomb Run-Visual IP Fly-Over

1. (P) When over IP, freeze button and target in¬
sert button - PUSH ON

2. Bomb release button - DEPRESS AND HOLD
(Offset Bomb)

3. (SUU-7) CBU lights - MONITOR

a. Blinking light - Tubes Remaining

b. Amber light out - All tubes have received
a firing pulse.

When the aircraft is on course to the target
and at the preplanned release altitude and
true airspeed, depress and hold the bomb
release button until bomb release occurs,
indicated by the illumination of the pullup
light.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

POST STRIKE

Before Landing

1. Master arm switch - SAFE

2. Station select - OFF

3. Gun & stores switch - NORMAL

4. Sight mode selector knob - STBY, or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

Armament Area (De-arming)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

A/B 45Y-1, Y-2, Y-4 SPRAY TANK DISPENSERS |F-4D)

PREFLIGHT

| Refer to part 4, figure 2-24.

INFLIGHT

DISPENSING

1. Delivery mode selector knob - DIRECT

2. Weapon selector knob - RKTS & DISP, SINGLE

3. Station select - LOADED STATIONS
a. Green light - ON

4. Arm nose tail switch - NOSE & TAIL

5. Master arm switch - ARM
a. Amber light - ON

Note

Placing the master arm switch to ARM arms
the A/B 45Y-1 tank causing an explosive
squib to discharge, thereby pressurizing the
bladder of liquid.

Once the A/B 45Y-1 is armed, it cannot be
de-armed and therefore must not be brought
back to base.

Note

• On the A/B 45Y-2 dry agent spray tank, en¬
ergizing the master arm switch causes the
agent container to be pressurized by ram
air for proper dissemination. The Y-2 tank
can be de-armed by positioning the master
arm switch to SAFE.

• On the A/B 45Y-4 dry agent spray tank, en¬
ergizing the master arm switch arms the
tank. The Y-4 tank can be de-armed by po¬
sitioning the master arm switch to SAFE.

6. Bomb button - DEPRESSED

7. Amber light -'MONITOR

a. Blinking amber light - spray remaining

b. Amber light out - no spray remaining

2-40

Change 1

T.O. 1F-4C-34-1-1

DISPENSER RELEASE

1. Wing tank jettison switch - JETT

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & store switch - NORMAL

4. Slight mode selector knob - STBY, or CAGE

5. All DCU-94/A station selector switches (5)
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

TMU-28/B SPRAY TANK |F-4D)

PREFLIGHT

| Refer to part 4, figure 2-24.

INFLIGHT

1. Weapon selector knob - A/G MISSILE (Not in
RKTS & DISP)

2. Arm nose tail switch - SAFE

3. Master arm switch - SAFE

DISPENSING

1. Station selector button(s) - SELECT LOADED
STATION(S)

a. Green light(s) - ON

2. Master arm switch - ARM

a. Amber light(s) remain - OFF

3. To extend boom, weapon selector knob - RKTS
& DISP/SINGLE

a. While boom is extending, amber light(s) -
ON STEADY

b. Boom fully extended, amber light(s) -
BLINKING

4 To begin dispensing, bomb button - DEPRESS
AND HOLD (8 sec)

5. To stop dispensing, bomb button - RELEASE

6. Weapon selector knob - A/G MISSILE (Not in
RKTS & DISP)

7. To retract boom, arm nose tail switch - NOSE
& TAIL

a. Amber light continues to blink after boom is
retracted.

Note

The amber light will continue to blink until
power is removed from the aircraft, except
when the station selector button is pushed
off. When the station selector button is
pushed on, the light will begin blinking again.

8. Station selector button(s) - PUSH OFF
a. Green and amber lights - OFF

DISPENSER RELEASE

1. Wing/Tank jettison switch - JETT

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & store switch - NORMAL

4. Sight mode selector knob - STBY, or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

Change 1

2-41

T.O. 1F-4C-34-1-1

PAU-7/A SPRAY TANK |F-4D)

PREFLIGHT

Refer to part 4, Cockpit Weapons Check and Exterior
Inspection (Spray Tanks A/B45Y-1, -2, -4, PAU-
7/A, TMU-28/B)

INFLIGHT

1. Weapon selector knob - A/G MISSILE (NOT
RKTS & DISP)

2. Arm nose tail switch - SAFE

3. Master arm switch - SAFE

DISPENSING

1. Station selector buttons - RO, LO, OR BOTH
AS REQUIRED

a. Green select light(s) - ON

2. Weapon selector knob - RKTS & DISP/SINGLE

3. Bomb mode selector knob - DIRECT

4. Master arm switch - ARM

5. To extend boom arm nose tail switch - NOSE &
TAIL

6. To dispense, bomb button - DEPRESS & HOLD
Tank will dispense with boom up or down.

7. To stop dispensing, bomb button - RELEASE

8. To retract boom, arm nose tail switch - TAIL
(90 sec)

9. Station selector button(s) - PUSH OFF (after
boom retract)
a. Green light(s) - OFF

10. Delivery mode select knob - OFF

DISPENSER RELEASE

1. Wing tank jettison switch - JETT

before landing

1. Master arm switch - SAFE

2. Station selector button(s) - OFF

3. Guns & store switch - NORMAL

4. Sight mode selector knob - STBY, or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

SUU-16/A, -23/A GUN POD |F-4D|

PREFLIGHT

Refer to part 4, Cockpit Weapons Check and Exterior
Inspection (SUU-16/A-23/A Gun Pod)

INFLIGHT

STRAFING

6. Station selector button(s) - PUSH ON

a. Green light(s) - ON (SUU-23 Prestart) I

7. Master arm switch - ARM

a. Amber light(s) - ON, RAT OUT (SUU-16) * I

The RAT will extend when the master arm
switch is placed to ARM.

8. Trigger switch - ACTUATE

1. Sight mode selector knob - A/G

2. Reticle depression counter - SET AIR-TO-AIR

Note

• If the optical sight is to be used, the OFF or
DIRECT position should be selected on the
delivery mode selector panel.

• Reference to the RAT (ram air turbine) is
applicable to the SUU-16/A gun pod only.

3. Gun clear switch - NONCLEAR or AUTO
CLEAR

4. Weapon selector knob - GUNS or AS REQUIRED

When BOMBS or RKTS & DISP are selected,
the guns and stores switch must be in guns
and stores to select the guns.

5. Guns and stores switch - NORMAL or GUNS &

STORES , .

When the weapon selector knob is positioned
to GUNS, the switch should be in NORMAL.

1. Sight mode selector knob - A/A

2. Gun clear switch - NONCLEAR or AUTO
CLEAR

3. Weapon selector knob - GUNS or AS REQUIRED

4. Guns and stores switch - NORMAL or GUNS &
STORES

5. Station selector button(s) - PUSH ON

a. Green light(s) - ON (SUU-23 Prestart) I

6. (P) Radar power - OPR

7. (P) Radar mode switch - AS REQUIRED

8. (P) Radar range - R1

9. Master arm switch - ARM _

a. Amber light(s) - ON, RAT OUT (SUU-16) |

The RAT will extend when the master arm
switch placed to ARM.

10. (P) Target lock-on - ACCOMPLISH

11. Trigger switch - ACTUATE

2-42

Change 3

T.O. 1F-4C-34-1-1

FINAL BURST SAFE GUNS
(Rounds Remaining)

1. Gun clear switch - AUTO CLEAR

2. Trigger switch - ACTUATE

3. Station selector button - PUSH OFF

a. Green light - OFF.

b. Amber light - OFF, RAT IN

The RAT will retract when the station se¬
lector button is pushed OFF.

4. Guns and stores switch - NORMAL

5. Master arm switch - SAFE

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & stores switch - NORMAL

4. Sight mode selector knob - ST BY or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

AGM-12B/C/E MISSILE |F-4D)

PREFLIGHT

| Refer to part 4, figures 2-20A and 2-26.

INFLIGHT

TRANSMITTER CHECK

Perform an airborne check as follows:

1. Delivery mode select knob - DIRECT

2. Station selector buttons - OFF
a. Green lights - OFF

3. Warning lights test sw - TEST

a. Station green and amber lights - ON

4. Weapon selector knob - AGM-12

5. Master arm switch - ARM

a. All station amber lights - OFF

6. Bomb button - DEPRESS

7. Control handle - TRANSMIT COMMANDS

The transmitter timer is energized for 50
± 10 seconds.

8. Master arm switch - SAFE

BEFORE MISSILE LAUNCH

1. (AC, P) Oxygen diluter selector - 100 PER¬
CENT

2. Weapon selector knob - AGM-12

3. Station selector button - DEPRESS
a. Green light - ON

MISSILE LAUNCH

1. Master arm switch - ARM
a. Station amber light - ON

2. Bomb button - DEPRESS (2 sec approx)

Depress and hold the bomb button until the
missile fires or until the launch is aborted
due to missile malfunction.

To immediately arm a second missile for re-attack:

3. Station selector button (just fired) - DEPRESS
a. Green light - OFF

4. Station selector button (next missile) - DE¬
PRESS

a. Green light - ON

b. Amber light - ON

MISSILE FLIGHT (AGM-12E)

To prevent AGM-12E warhead from functioning:

1. (P) Armament power circuit breaker - PULL
(6E, No. 2 panel)

If it is necessary to safe the missile, pull
circuit breaker 6E.

AFTER MISSILE ATTACK

1. Armament switches - OFF/SAFE

a. Master arm switch - SAFE

b. Station selector buttons - OFF

2. Emergency vent handle - CYCLE

Pull to de-pressurize, then push to pres¬
surize to cycle cockpit air in case of con¬
tamination by missile exhaust gases.

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & stores switch - NORMAL

4. Sight mode selector knob - ST BY, or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

Change 2

2-43

T.O. 1F-4C-34-1-1

SUU-20 BOMB/ROCKET DISPENSERS |F-4D|

PREFLIGHT

Refer to Cockpit Weapons Check and Exterior Inspec¬
tion, part 4

INFLIGHT

ROCKET DELIVERY

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Intrvl switch - .10 OR .14 ONLY

5. Station select - AS REQUIRED
a. Green light - ON

6. Weapon selector knob - RKTS & DISP

7. Master arm switch - ARM
a. Amber light - ON

BOMB DELIVERY

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - AS REQUIRED

4. Intrvl switch - .10 OR .14

5. Station select - AS REQUIRED
a. Green light - ON

6. Weapon selector knob - BOMBS/SINGLE/RIP -
PLE/TRIPLE

7. Master arm switch - ARM
a. Amber light - ON

* There is no cockpit indication to determine
that all bombs or rockets have been released
or fired.

* The intervalometers within the SUU-20 can¬
not be rehomed in flight for an attempt to re¬
lease or fire ahung bomb or rocket.

*Do not use an aircraft interval setting of 0.06.

BEFORE LANDING

1. Master arm switch - SAFE

2. Stations select - OFF

3. Guns & stores switch - NORMAL

4. Sight mode selector knob - STBY, or CAGE

5. All DCU-94/A station selector switches (5)
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DEARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

SUU-21/A BOMB DISPENSER |F-4D|

PREFLIGHT

Refer to part 4, cockpit weapons check and Exterior
Inspection (SUU-21/A) -

INTERIOR INSPECTION (DCU-94/A)

10. Option selector knob - SAFE

a. Loaded station warn light(s) - FLASHING
(doors closing)

b. Loaded station warn light(s) - OFF (doors
closed)

11. Option selector knob - OFF

Before applying external power:

1. All station select switches (5) - AFT

2. Station select switch guard - INSTALLED

If other munitions are aboard, the required
guard should be installed.

3. Master release lock switch - AFT

4. Option selector knob - OFF

5. Bomb mode select knob - OFF

6. (WSO) Nuclear store consent switch - SAFE

With the dispenser doors open, proceed as follows:

7. External power - APPLY

8. Generator switches - EXT ON

9. Lamp test button - PRESS

a. Warn and unlocked lights - ON

INFLIGHT

ON BOMB RANGE (DCU-94/A)

1. Option selector knob - SAFE

2. Loaded station selector switch - FORWARD
a. Loaded station WARN light - ON

3. (WSO) Nuclear store consent switch - REL/ARM
a. Loaded station WARN light - OFF

4. Option selector knob - GRD

a. Loaded station WARN light - FLASHING
(doors opening)

b. Loaded station WARN light - ON (doors open)

5. Delivery mode selector knob - AS REQUIRED

6. Weapon selector knob - NOT RKTS & DISP

2-44

Change 6

T.O. 1F-4C-34-1-1

Note

When the SUU-21/A dispenser is loaded on
the inboard stations bomb release will not
occur if the weapon selector knob is on RKTS
& DISP.

BEFORE BOMB RUN (DCU-94/A)

1. Master release lock switch - FORWARD
a. Loaded station UNLOCKED light - ON

2. Loaded station WARN light - ON

AFTER BOMB RELEASE (DCU-94/A)

Manual Operation

After each bomb release, the dispenser doors re¬
main open and additional switching procedures are
unnecessary. With the DIRECT bombing mode se¬
lected, the release system (pickle button) is hot. If
it is necessary to safe the system between runs,
place the master release lock switch AFT, and re¬
select FWD just prior to the next run.

Automatic Operation

1. At bomb release loaded station WARN light -
FLASHING

2. Loaded station WARN light - OFF (doors
closed)

3. Option selector knob - SAFE

4. Option selector knob - GRD

a. Loaded station WARN light - FLASHING

b. Loaded station WARN light - ON (doors open)

AFTER FINAL BOMB RELEASE (DCU-94/A)

1. (Auto mode) Loaded station WARN light -
FLASHING

2. (Auto mode) Loaded station WARN light - OFF
(doors closed)

3. Option selector knob - SAFE

a. (Man. mode) Loaded station WARN light -
FLASHING

b. (Man. mode) Loaded station WARN light -
OFF (doors closed)

4. Master release lock switch - AFT

a. Loaded station UNLOCKED light - OFF

5. Delivery mode selector knob - OFF

WARNING

If the dispenser doors do not close and all
bombs have not been expended, the aircraft
must be flown to avoid populated areas to the
greatest degree practicable.

AFTER LANDING (DCU-94/A)

To open dispenser doors, if required:

1. (P) Nuclear store consent switch - REL/ARM

2. Loaded station selector switch - FORWARD

3. Option selector knob - GRD

a. Loaded station WARN light - FLASHING

b. Loaded station WARN light - ON (doors open)

4. All electrical power - REMOVED

Note

All electrical power must be removed from
the aircraft before performing steps 5, 6
and 7 to preclude the dispenser doors from
closing.

5. Option selector knob - OFF

6. All station selector switches (5) - AFT

7. (P) Nuclear store consent switch - SAFE

SUU-21/A BOMB DISPENSER |M0DIFIED]|F-4D|

PREFLIGHT

These procedures consider the employment of SUU-
21/A dispensers modified for use with pedestal panel
controls and inboard (sta 2 and 8) carriage only.

Refer to part 4, Cockpit Weapons Check and Exterior
Inspection (SUU-21/A Dispenser).

INTERIOR INSPECTION

If the dispenser doors are open, close the doors as
follows:

1. External power - APPLY

2. Generator switches - EXT ON

3. Armament safety override - DEPRESS

4. Station select button(s) - DEPRESS
a. Station green light(s) - ON

5. Master arm switch - ARM

a. Station amber light(s) - ON

6. Arm nose tail switch - NOSE

a. Station amber light(s) - FLASHING (doors
closing)

b. Station amber light(s) - OFF (doors closed)

7. Station select button(s) - OFF

8. Master arm switch - SAFE

INFLIGHT

WEAPON RELEASE

1. Optical sight - SET

a. Mode selector - A/G

b. Reticle depression knob - SET AS RE¬
QUIRED

2. Delivery mode selector knob - AS REQUIRED

3. Weapon selector knob - BOMBS I

Change 4

2-44A/(2-44B blank)

T.O. 1F-4C-34-1-1

1 4. Station select button(s) - DEPRESS

5. Master arm switch - ARM
a. Amber light(s) - ON

6. Arm nose tail switch - N&T

a. Station amber light - FLASHING (doors
opening)

b. Station amber light - ON (doors open)

7. Bomb button - DEPRESS

AFTER FINAL BOMB RELEASE

1. Arm nose tail switch - NOSE

a. Station amber light - FLASHING (doors
closing)

b. Station amber light - OUT (doors closed)

2. Master, arm switch - SAFE

3. Station select - OFF

4. Delivery mode selector knob - OFF

5. Sight mode selector knob - STBY or CAGE

AFTER LANDING

To open SUU-21/A Dispenser Doors:

1. Armament safety override button - DEPRESS

2. Station select button(s) - DEPRESS

3. Master arm switch - ON

4. Arm nose tail switch - N&T

a. Station amber light(s) - FLASHING (doors
opening)

b. Station amber light(s) - ON (doors open)

5. Station select button(s) - OFF

6. Master arm switch - OFF

Change 4

2-45

T.O. 1F-4C-34-1-1

TDU-11/B TARGET ROCKET (5-INCH HVAR) (F-4DJ

PREFLIGHT missile, observe proper SW and READY light

indications, aircraft to target range, and

Refer to part 4. - P ro P er tone indication.

INFLIGHT before landing

1. Optical sight - SET AS DESIRED

2. Missile select switch - HEAT

3. Applicable SW light - ON

If the SW light indicates that the station con¬
taining the target rocket is not selected, ac¬
tuate the missile select switch to HEAT RE¬
JECT until the desired station is selected.

4. Missile arm switch - ARM
a. READY light - ON

5. Trigger switch - ACTUATE

After the target rocket is fired, maneuver
the aircraft to pursue the target rocket, mon¬
itor the aural tone in the head set, and pre¬
pare to launch the AIM-9B missile at the tar¬
get rocket. Prior to launching the AIM-9B

1. Master arm switch - SAFE

2. Station select - OFF

3. Gun & stores switch - NORMAL

4. Sight mode selector knob - STBY, or CAGE

5. All DCU-94/A station selector switches (5)
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

MODIFIED A/A 37U-15 TOW TARGET SYSTEM [F-4D1

PREFLIGHT

Refer to part 4.

INFLIGHT

PRE-TAKEOFF

To reduce rolling tendencies immediately after take¬
off, the following aileron trim positions are recom¬
mended. Trim settings are the same with or without
centerline tank.

a. Dart system on station 1, station 9 empty: 2.5
inches left aileron down (trim 2.5 seconds to right of
neutral), 1.5 inches right rudder (trim 1.5 seconds
to right of neutral).

b. Dart system or station 1, external fuel tank on
station 9: 3.5 inches right aileron down (trim 3.5
seconds to left of neutral), 1.0 inch left rudder (trim
1.0 second to left of neutral).

Note

The tow target system, carried on the left
outboard wing station, may induce 20° to 30°
errors in the remote compass transmitter.

Due to this effect, the DG mode on the com¬
pass controller should be selected.

TAKEOFF

Initiate a slow pitch rotation at 140 KIAS to obtain 8
pitch attitude indicated on the ADI for liftoff at 180
to 190 KIAS. Decrease thrust after gear and flap re¬
traction to ensure that 275 KIAS is not exceeded.

Note

Refer to T.O. 1F-4C-1 External Store Limi¬
tations for A/A 37U-15 Tow Target System
inflight limitations.

TARGET DEPLOYMENT

1. Select DG mode on compass controller.

2. Delivery mode selector knob - DIRECT

3. Weapon selector knob - BOMBS/SINGLE

4. Station select - LO
a. Green light - ON

5. Arm nose tail switch - SAFE

6. Master arm switch - ARM
a. Amber light - ON

7. Bomb button - DEPRESS

Depressing the bomb button once will launch
the target.

Do not attempt to deploy a damaged dart tar¬
get. Motion of the damaged target after re¬
lease is unpredictable. Possible contact with
the aircraft could be hazardous.

8. Master arm switch - SAFE
a. Amber light - OFF

The master arm switch should be on SAFE
to preclude inadvertent cable cut.

2-46

Change 7

T.O. 1F-4C-34-1-1

CABLE CUT

1. Master arm switch - ARM
a. Amber light - ON

2. Tow cable - CUT

a. (before Rev K) Bomb button - DEPRESS

b. (after Rev K) Arm nose tail switch - NOSE

3. Chase plane, acknowledge cable cut.

Emergency Cut

1. Arm nose tail switch - NOSE & TAIL or TAIL

2. Chase plane, acknowledge cable cut.

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Gun & store switch - NORMAL

4. Sight mode selector knob - STBY or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

LANDING WITH STOWED TARGET (DAMAGED OR
UNDAMAGED)

1. Flaps - 1/2

2. Angle of attack - 17 to 18 UNITS

(With wing tank use less than 17 units)

INFLIGHT PROCEDURES FOR BOMBING RANGE
SELECTED WEAPONS IF-4D |

These procedures are included for easy inflight ref¬
erence to support typical bombing, rocket, and strafe
missions on the bomb range. Aircrews are still re¬
quired to use appropriate checklists for preflight and
jettison operations. Only the numbered items need
be performed; sub-steps are added for clarity.

INFLIGHT

ROCKET LAUNCHERS AND SUU-20

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - AS REQUIRED

4. Intrvl switch - .10 OR .14

5. Station select - AS REQUIRED
a. Green light - ON

6. Weapon selector knob - BOMBS/SINGLE/RIP¬
PLE/TRIPLE

7. Master arm switch - ARM
a. Amber light - ON

BOMBS, SUU-20

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Intrvl switch - .10 OR .14 ONLY

5. Station select - AS REQUIRED
a. Green light - ON

6. Weapon selector knob - RKTS & DISP

7. Master arm switch - ARM
a. Amber light - ON

BOMBS, SUU-21/A (DCU-94/A)

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - AS REQUIRED

4. Weapon selector knob - BOMBS

5. Option selector knob - SAFE

6. Loaded station selector switch - FORWARD
a. WARN light - ON

7. (WSO) Nuclear consent switch - REL/ARM
a. WARN light - OFF

8. Option selector knob - GRD

a. WARN light - FLASH

b. WARN light - ON

9. Master release lock switch - FORWARD
a. UNLOCKED light - ON

Note

To reopen doors during automatic operation,
repeat steps 5 and 8.

After Final Release (DCU-94/A)

1. Option selector knob - SAFE
a. WARN light - FLASH/OFF

2. Master release lock switch - AFT
a. UNLOCKED light - OFF

3. Loaded station selector switch - AFT

4. (WSO) Nuclear consent switch - SAFE

BOMBS, SUU-21/A MODIFIED

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - AS REQUIRED

4. Weapon selector knob - BOMBS

5. Station select button(s) - DEPRESS

6. Master arm switch - ARM
a. Amber light(s) - ON

7. Arm nose tail switch - N&T

a. Station amber light(s) - FLASHING (doors
opening)

b. Station amber light(s) - ON (doors open)

To Close Doors

1. Arm nose tail switch - NOSE

a. Amber light - FLASHING, THEN OFF

Change 7

2-47

T.O. 1F-4C-34-1-1

STRAFE - SUU-16/A, 23/A, and M61A NOSE GUN

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - OFF/DIRECT

4. Station select - AS REQUIRED
a. Green light - ON

5. Weapon selector knob - GUNS/AS REQUIRED

6. Gun clear switch - AS REQUIRED

7. Guns and stores switch - AS REQUIRED

8. Master arm switch - ARM
a. Amber light - ON

RANGE departure

1. Sight mode selector knob - CAGED, STBY

2. Delivery mode selector knob - OFF

3. Station select - OFF

4. Master arm switch - SAFE

Change 1

"All data on pages

2-49 thru 2-62 including figures 2-9 thru 2-13 deleted.

2-48

T.O. 1F-4C-34-1-1

PART 3 NORMAL AIRCREW PROCEDURES

F-4E

TABLE OF CONTENTS

(AC) SYSTEM

Optical Sight Check .2-63

Optical Sight Malfunction Indications . . 2-65
Optical Sight Camera, KB-25/A .... 2-66A
(WSO) SYSTEM CHECK

WRCS BIT Check.2-67

Radar BIT (Refer to T.O. 1F-4C-
34-1-1A)

AN/APX-81 (Refer to T.O. 1F-4C-34-1-2
or T.O. 1F-4C-34-1-1CL-1)

COMBAT WEAPONS (Before T.O. 1F-4E-556)

Bombs.2-68

Direct Delivery Mode.2-68

Dive Toss/Dive Laydown.2-68

Laydown.2-69

Offset Bombing/Target Finding ... 2-69

LABS/Offset Bomb/Tgt Find .... 2-70

Loft Bombing - Ripple Release ... 2-71

Centerline Weapons Release (DCU-

94/A).2-72

Post Strike.2-72

Rockets.2-73

CBU and Flare Dispensers.2-73

Direct Delivery Mode.2-73

Dive Laydown.2-73

Laydown.2-74

Offset Bombing/Target Finding ... 2-74

Post Strike.2-75

A/B45Y-1, Y-2, Y-4 Spray Tank Dis¬
pensers .2-76

TMU-28/B Spray Tank.2-76

PAU-7/A Spray Tank.2-77

SUU-16/A, -23/A Gun Pods.2-77

M61A1 Nose Gun.2-78

AIM-4D, -7D/E/E-2. -9B/E Missiles
(Refer to T.O. 1F-4C-34-1-1A)

AGM-12B/C/E Missiles.2-79

AGM-45 Missile
(Refer to T.O. 1F-4C-34-1-1A)

MK 1 Mod 0 Guided Weapon
(Refer to T.O. 1F-4C-34-1-1A)

TRAINING EQUIPMENT (Before T.O. 1F-
4E-556)

SUU-20 Bomb/Rocket Dispensers.2-80

SUU-21/A Bomb Dispenser..2-81

SUU-21/A Bomb Dispenser (Modified). . 2-82

Modified A/A 37U-15 Tow Target

System.2-82

Inflight Procedures for Bombing Range

Selected Weapons.2-83

COMBAT WEAPONS (After T.O. 1F-4E-
556)

Bombs & SUU-20.2-85

Direct Delivery Mode.2-85

Dive Toss/Dive Laydown.2-85

Laydown.2-86

Offset Bombing/Target Find.2-86

LABS/Offset Bomb/Tgt Find .... 2-87

Loft Bombing - Ripple Release . . . 2-89

Centerline Weapons Release (DCU-

94/A).2-89

Post Strike.2-89

Rockets (Launchers & SUU-20).2-90

CBU and Flare Dispensers.2-90

Direct Delivery Mode.2-90

Dive Laydown.2-91

Laydown.2-91

Offset Bombing/Target Finding ... 2-92

Post Strike.2-93

A/B45Y-1, Y-2, Y-4 Spray Tank Dis¬
pensers .2-93

TMU-28/B Spray Tank.2-94

PAU-7/A Spray Tank.2-95

SUU-16/A, -23/A Gun Pods.2-95

M61A1 Nose Gun.2-96

AIM-4D, -7D/E/E-2, -9B/E Missiles
(Refer to T.O. 1F-4C-34-1-1A)

AGM-12B/C/E Missiles.2-96

AGM-45 Missile
(Refer to T.O. 1F-4C-34-1-1A)

MK 1 Mod 0 Guided Weapon
(Refer to T.O. 1F-4C-34-1-1A)
TRAINING EQUIPMENT (After T.O. 1F-
4E-556)

SUU-21/A Bomb Dispenser.2-81

SUU-21/A Bomb Dispenser (Modified). . 2-97

Modified A/A 37U-15 Tow Target

System.2-98

Inflight Procedures for Bombing Range
Selected Weapons.2-98A

OPTICAL SIGHT CHECK |F-4E|

accurate BIT check, gunsight BIT checks
should be performed only when the aircraft is
stopped or in level unaccelerated flight.

AC should position his head to the right until one-half
of the reticle is removed by the BIT 1 mask. The
BIT 2 mask must be rotated forward to remove the
top half of the reticle prior to selecting BIT 2. Radar
power must be available at least 30 seconds prior to
performing the BIT 2 check. For proper BIT check,
a 10-Mil sight depression must be used.

[ CAUTION {

1. Sight mode selector knob - STBY (Remain for
30 sec)

The sight mode switch should remain in
STBY for 30 seconds to provide warmup
power prior to selecting other modes; how¬
ever, this will not damage the set if not ac¬
complished.

2. (WSO) Radar power - TEST or STBY

To avoid gyro system damage and to get an

Change 9

2-63

T.O. 1F-4C-34-1-1

I CAUTION 1

< i<w 4

Radar power should remain in OFF until the
aircraft is operating on internal power and
the engines are up to 50% rpm minimum.

This will reduce specific diode failures with¬
in the radar pulse transmitter and provide
adequate cooling for radar components.

3. Sight shutter lever - OPEN

4. Sight mode selector knob - CAGE

Reticle should appear on the combining glass.

5. Reticle intensity control - CHECK

Check that the reticle intensity can be con¬
trolled.

6. Reticle depression counter - SET 10 MILS

7. Sight mode selector knob - CAGE to A/G to
A/A

a. Pipper at RBL, note position of pipper.

b. Check ± 2 mils between modes.

With the sight mode selector knob in CAGE,
note the position of the pipper on the ground,
then rotate the sight mode selector knob from
CAGE to A/G, and then to A/A. There should
not be more than 2 mils difference between
the three positions. This is a radar boresight
line (RBL).

Note

When the sight mode selector knob is posi¬
tioned to CAGED, A/A, A/G, it remains
caged to the radar boresight line regardless,
of the reticle depression counter setting.

This is true only when the aircraft is on the
ground; when airborne, the sight functions
normally.

8. Sight mode selector knob - BIT 1

a. The reticle should jump 25 ± 4 mils horizon¬
tally to the left (figure 2-14).

b. The roll tabs should rotate 90° clockwise.

c. The range bar should indicate 4000 feet (3
o'clock position).

Note

A 30-second warm-up period is required
prior to performing BIT 2.

9. Sight mode selector knob - BIT 2

a. The reticle should jump 25 ± 4 mils down
from the BIT 1 position (figure 2-17).

b. The range bar should indicate 6700 feet
(12:30 o'clock position).

c. Roll tabs should indicate level flight.

10. Sight mode selector knob - A/A

a. The pipper should return to the radar bore¬
sight line.

Optical Sight/Radar Tie-In (Before T.O. 1F-4E-540)

11. (AC) All armament switches - OFF/SAFE

a. Station green/amber lights - OFF

b. Weapon selector knob - BOMBS

CAGE,

BIT 2

Notes

a. 10 mils must be set into manual depression window
for proper read-out of BIT functions.

b. Rear cockpit radar power switch must be out of
"Off” position for at least 30 seconds.

4C-34-1-M136)

Figure 2-14

12. (AC) Armement safety override button - PUSH
IN

WARNING

When the armament safety override button is
energized, the jettison circuit is placed in an
inflight configuration, regardless of the land¬
ing gear handle position. The AC has a jetti¬
son capability during takeoff while weight is
on the gear.

13. (WSO) Radar range - R1

14. (WSO) Track switch - MANUAL

15. Radar mode selector knob - RDR

16. (WSO) Action switch HA, position gate at 2 NM
and depress to FA.

a. Range bar indicates 12,000 ft. (3 o'clock).

b. (WSO) Display switch - VI

c. VI meter reads greater than 9000 ft. (Range
rate is selected by manual Vc knob.)

17. (AC-WSO) Rotate manual Vc knob to obtain 200
knots closure; range bar begins moving toward
5 o'clock (6000 ft.) position.

18. (AC) Master arm switch - ARM (at 6000 ft.)

2-64

Change 5

T.O. 1F-4C-34-1-1

Note

After T.O. 1F-4E-534, the lead compute
mode may be obtained with master arm
switch in SAFE.

19. (AC) Weapon selector knob - GUNS (at 6000 ft.)

a. Range bar jumps to 1 o'clock.

b. Reticle slowly depresses 4 to 5 mils.

20. (AC-WSO) Compare VI meter range readout and
range bar as range decreases. Inside 4000 ft.

(3 o'clock), the pipper rises 4 to 5 mils as
range approaches 1500 feet. Stop the range
bar at 1500 feet (Vc knob zero closure).

21. (AC) Reticle cage (ARR) button - DEPRESS
AND HOLD

a. Pipper should not move more than one mil.

22. (WSO) Action switch - HA and RELEASE
a. Range bar - OFF

23. (AC) Reticle cage (ARR) button - RELEASE
a. Pipper should not move more than one mil.

24. (AC) Master arm switch - SAFE

25. (AC) Sight mode selector knob - STBY or
CAGE

CAUTION |

The sight should be caged for takeoff and
landing; select STBY or CAGE to prevent
damage to the mirror drive assembly.

26. (AC) Shutter lever - OFF (if leaving airplane)

If further use of the sight is not anticipated,
close the shutter to prevent sun light from
entering optical system.

I Optical Sight/Radar Tie-In (After T.O. 1F-4E-540,
Before T.O. 1F-4E-556)

11. (AC) All armament switches - OFF/SAFE
a. Station green/amber lights - OFF

b. Weapon selector knob - BOMBS

12. (AC) Armament safety override button - PUSH
IN

WARNING

When the armament safety override button is
energized, the jettison circuit is placed in an
inflight configuration, regardless of the land¬
ing gear handle position.

13. (WSO) Radar power - TEST

14. (WSO) Test - 1

15. (WSO) Radar range - R1

16. (WSO) Track switch - AUTO

17. (WSO) Radar mode selector knob - RDR

18. (WSO) Action switch HA, position gate at first
tgt and depress to FA.

a. (AC) Range bar indicates 6000 ft. (5 o'clock).

b. (AC) VI meter reads 6000 ft.

19. (AC) Weapon selector knob - GUNS

a. Range bar jumps to 1 o'clock (6000 ft.). The
sight switches out of triple ranging.

b. Reticle slowly depresses 4 to 5 mils. The
pipper is moving from RBL (missiles) to
lead compute (guns).

20. (AC) Reticle cage (ARR) button - DEPRESS
AND RELEASE

a. Pipper moves up to 1500 range and returns
to 6000 ft. range.

b. Range bar continues to read 6000 ft.

(1 o'clock)

21. (WSO) Action switch - HA and RELEASE

a. (AC) Pipper moves from 6000 ft to 1500 ft.
range.

b. (AC) Range bar - OFF

22. (AC) Sight mode selector knob - STBY or
CAGE

I^CMjrnor^

The sight should be caged for takeoff and
landing: select STBY or CAGE to prevent
damage to the servoed mirror and the gyro
gimbals.

23. (AC) Shutter lever - CLOSE (if leaving airplane)

If further use of the sight is not anticipated,
close the shutter to prevent sun light from
entering optical system.

Optical Sight/Radar Tie-In (After T.O. 1F-4E-556)

11. (AC) All armament switches - OFF/SAFE

a. Station green/amber lights - OFF

b. Heads up ARM light - OFF

c. Weapon selector knob - BOMBS

12. (AC) Armament safety override button - PUSH
IN

WARNING

When the armament safety override button is
energized, the jettison circuit is placed in an
inflight configuration, regardless of the land¬
ing gear handle position.

13. (AC) Guns/missile select - RADAR
a. Heads up RADAR light - ON

14. (WSO) Radar power - TEST

15. (WSO) Test - 1

16. (WSO) Radar range - R1

17. (WSO) Track switch - AUTO

18. (WSO) Radar mode - BST

19. (AC) Auto-acq sw - DEPRESS and RELEASE

a. Radar locks on first target.

b. (AC) Range bar indicates 6000 ft. (5 o'clock).

c. (AC) VI meter reads 6000 ft.

20. (AC) Guns/missiles sel - GUNS
a. Heads up GUN light - ON

Change 5

2-64A

T.O. 1F-4C-34-1-1

b. Range bar jumps to 1 o'clock (6000 ft.). The
sight switches out of triple ranging.

c. Reticle slowly depresses 4 to 5 mils. The
pipper is moving from RBL (missiles) to
lead compute (guns).

21. (AC) Cage button - DEPRESS AND RELEASE

a. Pipper moves up to 1000 range and returns
to 6000 ft. range.

b. Range bar continues to read 6000 ft.

(1 o'clock)

22. (WSO) Action switch - HA and RELEASE

a. Radar breaks lockon.

b. (AC) Pipper moves from 6000 ft to 1000 ft.
range.

c. (AC) Range bar - OFF

23. (AC) Sight mode selector knob - STBY or

CAGE

CAUTION }

The sight should be caged for takeoff and
landing: select STBY or CAGE to prevent
damage to the mirror drive assembly.

24. (AC) Shutter lever - CLOSE (if leaving airplane)
If further use of the sight is not anticipated,
close the shutter to prevent sun light from
entering optical system.

2-64B

Change 5

T.O. 1F-4C-34-1-1

OPTICAL SIGHT MALFUNCTION INDICATIONS

RETICLE

ELEVATION

RETICLE

AZIMUTH

RETICLE

MOTION

BIT MODE

MALFUNCTION

OPTICAL SIGHT STATUS

BIT 1

Reticle goes to +10 mils
with -10 set in the man¬
ual depression control.

The manual depression CDX is
functioning, but cannot be manually
adjusted. Sight is useless for

WRCS laydown, dive bombing,rock¬
ets, air-to-ground, and guns air
to ground.

Dive toss, dive laydown, missile
and guns air-to-air and offset
bombing modes are operational.

BIT 2

Reticle remains at RBL.

There is either no effect, or all
modes except WRCS laydown mis¬
siles and guns air-to-air, and off¬
set bomb will be inoperative.

BIT I

Reticle drives to bottom
of the combining glass.

All modes are inoperative.

BIT 1

Reticle drives 35 mils
to top of the combining
glass.

WRCS laydown may be affected.

BIT 2

Reticle drives down but
not to 25 mils.

Correct lead angles are not being
generated and lead computing op¬
eration is in error.

BIT 1

Reticle remains at RBL.

The sight may remain at the RBL
in all modes. It is also possible
that the sight may not respond to
drift signals applied to dive laydown
WRCS laydown, or dive toss. How¬
ever, lead computing operation is
unaffected.

BIT 1 and
BIT 2

Reticle travels to ex¬
treme left of combining
glass.

Lead computations are incorrect.

BIT 2

Reticle remains at RBL
in azimuth after being

25 mils to left in BIT 1.

BIT malfunction - should not affect
lead computing mode.

BIT 1 and
BIT 2

Reticle remains at RBL
in elevation and azimuth.

The reticle may remain fixed at the
RBL in all modes.

BIT 1 and
BIT 2

Jittery Reticle.

Open loop from tachometer. This
defect will be present in all modes
of operation.

Figure 2-15 (Sheet 1 of 2)

2-65

T.O. 1F-4C-34-1-1

OPTICAL SIGHT MALFUNCTIOH INDICATIONS (CONT .)

ITEM

BIT MODE

MALFUNCTION

OPTICAL SIGHT STATUS

RANGE

BAR

BIT 1 and
BIT 2

Range bar is in stow
position.

Analog bar will remain stowed in
all modes of operation and lead
computing operation will not be
possible.

BIT 1

Range bar is at 1500'
position.

BIT malfunction - the analog bar
should function properly in all op¬
erational modes. Ranging and lead
computation may be correct.

BIT 2

Range bar is at 1000'
or 4000' position.

BIT 1 and
BIT 2

Range bar keeps driving.

Open loop - no feedback voltage
from the follow-up pot. This defect
will be present in all modes of op¬
eration.

BIT 1 and
BIT 2

Range bar is jittery.

No tachometer feedback to stabilize
servo amplifier. This defect will
be present in all modes of operation.

BIT 1 and
BIT 2

Range bar sticks.

Probably a mechanical bind is pres¬
ent. No mode of operation will be
free of this defect.

ROLL

TABS

BIT 1

Roll TABs remain at
wings level.

BIT malfunction, the roll tabs may
or may not work in flight.

BIT 1 and
BIT 2

Roll tabs rotate con¬
tinuously.

Open loop - no feedback signal.

Roll loop will not function in any
mode of operation.

BIT 1 and
BIT 2

Jittery roll tabs.

No tachometer feedback. This de¬
fect will show up in all modes of
operation.

F4E-34—M-309-2

Figure 2-15 (Sheet 2 of 2)

2-66

T.O. 1F-4C-34-1-1

OPTICAL SIGHT CAMERA, KB-25/A

1. (AC-WSO) Gun camera switches - OFF

2. Film magazine - INSTALLED

a. Push button (upward) in center of film maga
zine.

b. Slide magazine in, and release button.

3. Frames per second switch (table) - 24 (down)
or 48 (up).

4. Aperture control (table) - SET

5. Camera overrun switch - 0, 3, 10, or 20 sec.

6. Camera run button (right side) - DEPRESS

a. Observe motor knob (left side) - ROTATE

b. Observe magazine footage indicator.

Note

To conserve film, steps 6 and 6a may be ac¬
complished without a magazine installed.

With 100 feet of film, camera run time is
2.46 minutes at 24 fps, or 1.23 minutes at
48 fps.

BASED ON EKTACHROME MS FILM, ASA 64

MISSION

LIGHT

CONDITIONS

FRAME

RATE

(F.P.S.)

APERTURE

Air-to-

Daylight

f/8

air

f/5.6

♦Subdued

f/2.8

Air-to-

Daylight

f/H

ground

f/8

♦Subdued

f/4

f/2.8

♦Overcast, or just before dusk or dawn.

Change 7

2-66A/(2-66B blank)

T.O. 1F-4C-34-1-1

WRCS BIT CHECK |F-4E|

1. Delivery mode selector knob - OFF

2. HSI mode switches - NAV COMP

3. (WSO) Weapon delivery panel switches - SET

a. Activate switch - NORMAL

b. Tgt find switch - NORMAL

c. Range switch - X100

4. (WSO) Control panel counters - SET

a. Target distance N/S - N274

b. Target distance E/W - El 14

c. Target alt range - 170

d. Drag coefficient - 2.00

e. Release advance - 900

f. Release range - 050

(Use 500 if step 3c is X10)

Note

c. After 5 seconds, freeze button - PUSH ON

d. Miles counter begins to decrease.

e. Approach indicator should indicate a pullup
command (LOW).

f. After 10 seconds, approach indicator should
indicate a level command (CENTER).

g. After 5 seconds - GO/NO-GO

h. After 5 seconds, approach indicator should
indicate a dive command (HIGH)

14. (WSO) BIT selector knob - TGT FIND OFFSET

BOMB

a. (WSO) BIT button - PUSH and HOLD

The BIT button must be held depressed
without interruption until completion of
step 14 m.

A NO-GO indication will occur if the above
parameters are not used during BIT.

I CAUTION

5. (WSO) INS mode selector knob - ALIGN or NAV

6. (WSO) BDHI mode switch - NAV COMP

7. (WSO) Radar mode switch - MAP-PPI

8. (WSO) Radar range switch - R2

9. (WSO) Radar power - STBY

CAUTION

Radar power should remain in OFF until the
aircraft is operating on internal power and
the engines are up to 50% rpm minimum.

This will reduce specific diode failures with¬
in the radar pulse transmitter.

10. (WSO) BIT selector knob - LAYDOWN, PUSH

and HOLD

a. Freeze button - PUSH ON (after 5 sec)

b. Range indicator illuminates.

c. After 15 seconds - GO/NO-GO

11. (WSO) BIT selector knob - DIVE LAYDOWN,

PUSH and HOLD

a. Freeze button - PUSH ON (after 5 sec)

b. After 15 seconds - GO/NO-GO

12. (WSO) BIT selector knob - DIVE TOSS, PUSH

and HOLD

a. Freeze button - PUSH ON (after 5 sec)

b. After 15 seconds - GO/NO-GO

13. (WSO) BIT selector knob - AGM-45, PUSH and

HOLD

a. BDHI and HSI miles counter - 7.6 ± 0.5 NM

b. Alt indicator illuminates.

I CAUTION 1

When the BIT button is depressed, the WRCS
computer receives an aircraft altitude input
that is higher than the target altitude inserted
in step 4c. Upon completion of the BIT check,
the target altitude/range counter must be set
to 000. This is necessary to avoid possible
damage to the WRCS pitch servo.

b. (WSO) Along track cursor control - MOVE
(after 5 sec)

Move the along track cursor control first
in a forward direction to cause the along
track cursor to appear and move well up
on the scope before stopping it by releas¬
ing the cursor control. Improper opera¬
tion of the along track cursor control can
cause the WRCS computer to function as
though the RIP were behind the aircraft;

i.e., the cross track cursor responds in a
reverse direction to that normally obtained
when the cross track cursor control is op¬
erated.

c. (WSO) Cross track cursor - MOVE

Outboard movement of the cross track
cursor control causes the cursor to move
to the right.

d. (WSO) Reset button - PUSH

e. (WSO) Cursors should return to center cross
track and zero range.

f. (WSO) Target insert button - PUSH ON

g. (WSO) Along track cursor; 6.5 miles on 0°
grid line (± 2000 feet). Before T.O. 1F-4E-
540; cross track cursor, right 20° ± 1.5°.
After T.O. 1F-4E-540; cross track cursor,
right 30° ± 1.5°.

h. (AC) HSI bearing pointer should read 23° ±
2.5° to the right of the lubber line and the
TGT mode light on the HSI illuminates.

i. (WSO) BDHI No. 1 needle should read 23° ±

* 2.5° to the right of the top index.

j. (AC-WSO) HSI and BDHI miles counters
should read 4.8 ± 1.0 NM.

Change 8

2-67

T.O. 1F-4C-34-1-1

k. ADI vertical pointer should deflect full right
of center.

l. (WSO) Freeze button - PUSH ON.

Miles counter decreases to zero, then in¬
creases. The roll tabs rotate as the HSI
miles counter passes through zero.

m. (WSO) After 15 seconds - GO/NO-GO

15. (WSO) WRCS control panel counters - RESET

a. Target distance N/S - N243

b. Target distance E/W - E/W Zero

c. Target alt range - 243

16. (WSO) Radar power - TEST

17. (WSO) Test switch - TEST 1

18. (WSO) WRCS BIT button - PUSH and HOLD

a. (WSO) Reset button - PUSH

b. (WSO) Target insert button - PUSH ON

c. (WSO) Along track cursor; 5.0 miles, checked
against the 5th BIT target. The near
edges of each should exactly coincide. Radar
receiver gain must be reduced to observe
the along track cursor.

d. (AC-WSO) Crosstrack cursor; zero azimuth
(± 1.5°). Note the actual position of the azi¬
muth cursor for in-flight evaluation of air¬
craft steering indicators (BDHI-HSI-ADI).

e. HSI bearing pointer should read under air¬
craft lubber line (± 2.5°), sight roll tabs
level, and ADI vertical pointer centered.

f. (WSO) BDHI No. 1 needle under lubber line
(± 2.5°).

19. (WSO) WRCS BIT selector knob - RELEASE
and OFF

Release the BIT button and position the BIT
selector knob to OFF.

20. (WSO) Target alt/range counter - set 000

Note

• The B-sweep may not be centered on the
scope because of erroneous drift inputs to
the radar MAP-PPI and A/G mode when per¬
forming this BIT check on the ground.

• If aircraft power is interrupted or fluctuates
during a BIT check, a NO-GO indication may
result and the BIT check should be repeated.

• Disregard the NO-GO indication when a NO-
GO indication is received as the WRCS BIT
button is released, if a GO indication was
received while the BIT button was held ener¬
gized.

21. (WSO) Weapon delivery panel - CHECK

a. Target find switch - NORM

b. Range switch - NORM

22. (WSO) Radar power - AS REQUIRED

BOMBS (F-4E)

PREFLIGHT

Refer to part 4.

INFLIGHT

Note

After T.O. 1F-4-750 (BRU-5/A centerline
rack), the following release procedures may
be used to release the M118 or MK 84 GP
bombs from the CL station. On unmodified
aircraft, the DCU-94/A procedures may be
used.

DIRECT DELIVERY MODE

Emergency Bomb Release

1. Weapon selector knob - BOMB/RIPPLE

2. Repeat above steps 5 thru 9, hold bomb button
depressed 4 seconds.

If all bombs do not release:

3. Weapon selector knob - RKTS & DISP

4. Weapon selector knob - BOMB/RIPPLE

5. Bomb button - DEPRESS (hold 4 seconds)

DIVE TOSS/DIVE LAYDOWN
Before Bomb Run

Bomb Release-Armed

1. Delivery mode selector knob - DIRECT

2. Sight mode selector knob - A/G

3. Reticle depression knob - SET

4. Weapon selector knob - BOMBS

5. Arm nose tail switch - SET

6. Intrvl switch - SET (if applicable)

7. Station selector - LOADED STATION
a. Green light(s) - ON

8. Master arm switch - ARM
a. Amber light(s) - ON

9. Bomb button - DEPRESS

a. Pullup light - ON

b. When station is empty, amber light - OFF

1. Delivery mode selector knob - DIVE TOSS or
DIVE LAY

2. Sight mode selector knob - A/G

The sight reticle is electrically caged to the
radar boresiglit line and is drift stabilized.

3. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

4. (WSO) INS mode selector knob - NAV

5. (WSO) Radar mode selector knob - AIR-GND

6. (WSO) Radar range - R1 or R2

7. (WSO) Radar power - OPR

B-sweep, acquisition symbol, and el strobe
centered on scope.

8. (WSO) Antenna stab switch - NOR

2-68

Change 7

T.O. 1F-4C-34-1-1

9. (P) Maneuver switch - HI-G

10. (P) WRCS drag coefficient counter - SET
(Dive Toss Only)

11. (P) WRCS release range counter - SET
(Dive Lay Only)

a. Range switch - NORM or X100

12. (P) WRCS release advance - SET (if required)

13. Weapon selector knob - BOMBS

14. Arm nose tail switch - SET

15. Intrvl switch - SET (if required)

Note

16. Station selector button(s) - PUSH ON

a. Green light(s) - ON

17. Master arm switch - ARM
a. Amber light(s) - ON

Bomb Run

1. (P) Receiver gain - MINIMUM

2. (P) Lockon target (CALL)

3. Bomb release button - DEPRESS AND HOLD

a. After bomb release, pullup light - ON

b. After station is empty, amber light - OFF

During the initial dive toward the target
area, the pilot reduces the receiver gain
to obtain a single return, depress the ac¬
tion switch to Half Action, place the range
strobe in the center of the return, and then
depress the action switch to Full Action
and release. After lockon, the AC places
the pipper on target, depresses and holds
the bomb release button, and initiates the
desired delivery maneuver. After the bomb
is automatically released, the pullup light
will illuminate and will go out when the
bomb button is released. The amber light
will go out when the station is empty.

LAYDOWN

Before Bomb Run

1. Delivery mode selector knob - LAYDOWN

2. Sight mode selector knob - A/G

3. Reticle depression counter - SET (if required)

Set the IP-to-target sight setting.

4. HSI mode switches - NAV COMP

If the HSI steering information is to be used,

the NAV COMP position must be selected.

5. (P) INS mode selector knob - NAV

6. (P) WRCS target range counter - SET

Set the distance from IP to target.

7. (P) WRCS release range counter - SET
a. Range switch - NORM or XI00

8. (P) WRCS release advance counter - SET (if
required)

9. Weapon selector knob - BOMBS

10. Arm nose tail switch - SET

11. Intrvl switch - SET (if required)

12. Station selector button(s) - PUSH ON
a. Green light - ON

13. Master arm switch - ARM
a. Amber light - ON

Bomb Run

Approach the target at the preplanned release alti¬
tude and airspeed. When the aircraft is directly over
the IP, or when the pipper is on target, depress and
hold the bomb release button. Maintain a constant
airspeed, altitude, and course until the bomb is
automatically released. The pullup light will illumi¬
nate to indicate bomb release and will go out when
the bomb button is released. Wind corrections for
the bomb must be applied prior to depressing the
bomb button.

1. Bomb release button - DEPRESS AND HOLD

a. At bomb release, pullup light - ON

b. When a station is empty, amber light - OFF

OFFSET BOMBING/TARGET FIND
Before IP

1. Delivery mode selector knob - OFFSET BOMB
or TGT FIND

2. Sight mode selector knob - A/G

The optical sight reticle is electrically caged
to the RBL and to 0° in azimuth. The roll
tabs display aircraft attitude until target in¬
sert, then steering commands to the target.

3. Navigation mode selector knob - NAV COMP

4. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

5. (P) INS mode selector knob - NAV

6. (P) BDHI mode switch - NAV COMP

7. (P) Weapon delivery panel - SET

a. Activate switch - NORMAL

b. Tgt Find switch - NORMAL

c. Range switch - AS REQUIRED

Note

The position of the range switch will affect
the value placed in the release RANGE read¬
out: times 10 (NORMAL), or times 100.

8. (P) WRCS input counters - SET

a. Target distance N/S -100-ft increments.

b. Target distance E/W -100-ft increments.

c. IP altitude MSL - 100-ft increments.

d. Release range - 10-ft or 100-ft increments
(Offset bomb)

e. Release advance - Milliseconds (Offset bomb,
if required)

9. Weapon selector knob - BOMBS (Offset bomb)

Note

The ADI will not provide steering if the
weapon selector knob is on AGM-45.

10. Arm nose tail switch - SET

11. Intrvl switch - SET (if required)

Change 1

2-69

T.O. 1F-4C-34-1-1

12. Station selector button(s) - PUSH ON

a. Green light - ON

13. Master arm switch - ARM
a. Amber light - ON

Bomb Run-Offset Radar IP

1. (P) Radar power - OPR

2. (P) Radar mode switch - MAP-PPI

3. (P) Antenna stab switch - NOR

4. (P) Cursor intensity - ADJUST

5. (P) Antenna elevation - ADJUST

6. (P) Scan switch - WIDE

7. (P) Radar range selector knob - R2 or R3

8. (P) Operate the along track cursor to position
the range cursor over the RIP.

9. (P) Operate the cross track cursor to position
the offset cursor over the RIP.

10. (P) Freeze button - PUSH ON

Note

• The along track cursor must be moved first
to initiate cursor control. Position the inter¬
section of the cursors over the RIP and then
push the freeze button ON; the cursors begin
tracking the RIP. The cursors can be moved
to touch-up the intersection location over the
RIP after the Freeze button is pushed on.

• Do not position the range cursor below zero
range. If the range cursor is moved below
zero range and then moved out over the IP,
the steering information will be in error by
180 even though the cursor responds nor¬
mally to along track cursor control move¬
ments.

11. (P) Target insert button - PUSH ON

12. Bomb release button - DEPRESS AND HOLD

(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, amber light - OFF

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

Bomb Run-Visual IP Fly-Over

1. (P) When over IP, freeze button and target in¬
sert button - PUSH ON

2. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, amber light - OFF

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

labs/offset bomb/tgt find

After Takeoff

1. Delivery mode selector knob - OFFSET BOMB
or TGT FIND

2. (P) Target find switch - HOLD

Select HOLD on the weapon delivery panel.

3. Sight mode selector knob - A/G

The optical sight reticle is electrically caged
to the RBL and to 0 in azimuth. The roll
tabs display aircraft attitude until target in¬
sert, then steering commands to the target.

4. Navigation mode selector knob - NAV COMP

5. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

6. (P) INS mode selector knob - NAV

7. (P) BDHI mode switch - NAV COMP

8. (P) WRCS input counters - SET

a. Target distance N/S - 100-ft increments

b. Target distance E/W - 100-ft increments

c. IP altitude MSL - 100-ft increments

d. Release range - 10-ft or 100-ft increments
(Offset bomb)

e. Release range - LABS pullup range, 10-ft
or 100-ft increments

Note

The (X100) factor is selected through the
range switch on the weapon delivery panel.

f. Release advance - Milliseconds (Offset bomb,
if required)

9. Weapon selector knob - BOMBS (Offset bomb)

2-70

Change 1

T.O. 1F-4C-34-1-1

Note Note

The ADI will not provide steering if the
weapon selector knob is on AGM-45.

10. Arm nose tail switch - SET

11. Intrvl switch - SET (if required)

12. Station selector button(s) - PUSH ON
a. Green light - ON

13. Master arm switch - ARM
a. Amber light - ON

14. (P) Dual timers - SET

a. Pullup timer - Ti

b. Release timer - T2

15. (P) Release gyro - SET

a. Low angle (LOFT) - DEG

Before Bomb Run

1. (P) Radar power - OPR

2. (P) Radar mode switch - MAP PPI

3. (P) Antenna stab switch - NOR

4. (P) Cursor intensity - ADJUST

5. (P) Antenna elevation - ADJUST

6. (P) Scan switch - WIDE

7. (P) Radar range selector knob - R2 or R3

Bomb Run-Offset Radar IP

1. (P) Operate the along track control to position
the range cursor over the RIP.

2. (P) Operate the cross track control to position
the offset cursor over the RIP.

3. (P) Freeze button - PUSH ON

Note

•The along track cursor must be moved first
to initiate cursor control. Position the inter¬
section of the cursors over the RIP and then
push the freeze button ON; the cursors begin
tracking the RIP. The cursors can be moved
to touch-up the intersection location over the
RIP after the Freeze button is pushed on.

4. (P) Target insert button - PUSH ON

5. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, amber light - OFF

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

Bomb RunVisual IP Fly-Over

1. (P) When over IP, freeze button and target in¬
sert button - PUSH ON

2. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, amber light - OFF

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

Bomb Run Labs/TGT Find

1. Delivery mode selector (LABS) - AS REQUIRED

Select the planned delivery mode.

Note

With the TGT find switch on HOLD, the de¬
livery mode selector may be positioned to any
LABS mode without losing WRCS function.

2. (P) Along track and cross track controls - AS
REQUIRED (Visual or Radar IP)

3. (P) Freeze control - PUSH ON

4. (P) Target Insert control - PUSH ON

5. (P) After target insert, activate switch - ON

Select the ON position only after steering in¬
struments have transitioned to target.

6. At warning tone (Ti start) - MIL POWER
PULLUP

7. Bomb button - DEPRESS AND HOLD

LOFT BOMBING-RIPPLE RELEASE

Before Bomb Run

1. (P) Activate switch - NORMAL

When the WRCS is not used with the LABS
modes, the target find switch and/or the
activate switch on the weapons delivery panel
must be positioned to NORMAL.

Change 1

2-71

T.O. 1F-4C-34-1-1

2. (P) Low angle knob - SET

3. (P) Pull up timer - SET

4. (P) Release timer - SET ZERO

5. Delivery mode selector knob - LOFT

6. Pedestal panel - SET

a. Weapon selector knob - BOMB/RIPPLE

b. Arm nose tail switch - NOSE & TAIL

c. Intrvl switch - SET

d. Station selector button(s) - PUSH ON
(1) Green light - ON

e. Master arm switch - ARM
(1) Amber light - ON

At IP

1. Bomb button - DEPRESS AND HOLD

The bomb button must be energized until the
final bomb is released.

2. At pullup point, throttles - FULL MIL POWER

Loft Bomb Delivery

Approach the IP at the preplanned altitude and true
airspeed. When over the IP, depress and hold the
bomb button energized until the final bomb is re¬
leased. When the bomb button is depressed, the
pullup light will illuminate, the pullup timer will be¬
gin, and the ADI pointers will center. Upon comple¬
tion of the pullup timer, the pullup light and the
reticle light will go out and the horizontal pointer will
begin programming a 4-G pullup. This is the signal
to the AC to select full military power and begin ro¬
tation into the pullup maneuver by flying the ADI
pointers (4-G pullup) or the accelerometer. Since
the sight reticle is pitch stabilized, it will not be in
view above loft angles of 20 . When the aircraft atti¬
tude is at the preselected release angle, the pullup
light and the reticle light illuminate and the bombs
will begin releasing in a ripple sequence. After the
final bomb is released, the bomb button is released
and the AC initiates a wingover escape maneuver to
achieve a 120° turn while diving toward minimum
escape altitude. When the bomb button is released,
the pullup light will go out, and the horizontal pointer
will move out of view.

After Escape Maneuver

1. Master arm switch - SAFE

2. Station selector buttons (5) - OFF

3. Delivery mode selector knob - OFF

Placing the delivery mode selector knob to
OFF removes power from the bombing timers.

CENTERLINE WEAPON RELEASE (DCU-94/A)

Before Bomb Run

1. Delivery mode selector knob - DIRECT or AS
REQUIRED

2. Optical sight - SET (if required)

3. (P) Nuclear store consent switch - REL/ARM

4. DCU-94/A CL station selector switch - FOR¬
WARD

5. Arm nose tail switch - ARM

Bomb Run

1. DCU-94/A master release lock switch - FOR¬
WARD

a. CL UNLOCKED light - ON

2. Master arm switch - ARM

The master arm switch allows power to the
arm nose tail switch.

3. Delivery maneuver - EXECUTE

If the DIRECT delivery mode is selected, the
bomb is released when the bomb button is
depressed.

Note

If the bomb does not release, recheck switch
positions, select the DIRECT release mode
and depress bomb button, or energize the
nuclear store jettison control.

POST STRIKE
Before Landing

1. Master arm switch - SAFE

2. Station select - OFF

3. Gun & stores switch - NORMAL

4. Sight mode selector knob - STBY or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

Armament Area (De-Arming)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

2-72

Change 1

T.O. 1F-4C-34-1-1

ROCKETS (F-4E|

PREFLIGHT

| Refer to part 4, figure 2-22.

INFLIGHT

ROCKET FIRING

1. Delivery mode selector knob - DIRECT

2. Sight mode selector knob - A/G

3. Reticle depression knob - SET

4. Weapon selector knob - RKTS & DISP/SINGLE

5. Station select - LOADED STATIONS
a. Green light - ON

6. Master arm switch - ARM
a. Amber light - ON

7. Bomb button - DEPRESS

LAUNCHER RELEASE

1. Delivery mode selector knob - DIRECT

2. Weapon selector knob - BOMBS/RIPPLE

3. Repeat above steps 5, 6, and 7, hold bomb but¬
ton depressed 4 seconds.

a. When station is empty, amber light - OFF

If all launchers do not release:

4. Weapon selector knob - RKTS & DISP

5. Weapon selector knob - BOMBS/RIPPLE

6. Bomb button - DEPRESS (Hold 4 seconds)

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Gun & stores switch - NORMAL

4. Sight mode selector knob - STBY or CAGE

5. All DCU-94/A station selector switches (5)
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

CBU AND FLARE DISPENSERS (F-4E)

PREFLIGHT

Dispenser Release

| Refer to part 4, figure 2-23.

INFLIGHT

DIRECT DELIVERY MODE

1. Delivery mode selector knob - DIRECT

2. Weapon selector knob - BOMBS/RIPPLE

3. Repeat above steps 6 thru 9, hold bomb button
depressed 4 seconds

Dispensing

If all dispensers do not release:

1 .

2 .

6 .

8 .
9.

Delivery mode selector knob - DIRECT
Sight mode selector knob - A/G
Reticle depression knob - SET
Weapon selector knob - RKTS & DISP
a. (SUU-13, -38, -42) Weapon selector knob
- RKTS & DISP/SINGLE
(SUU-7) Intrvl switch - SET (if required)
Station select - LOADED STATIONS
a. Green light - ON
Master arm switch - ARM
a. Amber light - ON

Bomb button - DEPRESS AND HOLD AS RE¬
QUIRED

SUU-7 CBU lights - MONITOR

a. Blinking light - Tubes Remaining

b. Amber light out - All tubes have received a
firing pulse.

Note

v , _. The CBU lights will not monitor the empty

status of the flare dispenser, SUU-13,
SUU-38, SUU-42.

4. Weapon selector knob - RKTS & DISP

5. Weapon selector knob - BOMBS/RIPPLE

6. Bomb button - DEPRESS (Hold 4 seconds)

DIVE LAYDOWN
Before Bomb Run

1. Delivery mode selector knob - DIVE LAY

2. Sight mode selector knob - A/G

The sight reticle is electrically caged to the
radar boresight line and is drift stabilized.

3. HSI mode switches - NAV COMP

If the HSI indications are to be used, the
NAV COMP position must be selected.

4. (P) INS mode selector knob - NAV

5. (P) Radar mode selector knob - AIR-GND

6. (P) Radar range - R1 or R2

7. (P) Radar power - OPR

B-sweep, acquisition symbol, and el strobe
centered on scope,

8. (P) Antenna stab switch - NOR

Change 1

2-73

T.O. 1F-4C-34-1-1

9. (P) Maneuver switch - HI-G

10. (P) WRCS release range counter - SET

a. Range switch - NORM or X100

11. (P) WRCS release advance - SET (if required)

12. Weapon selector knob - RKTS & DISP

a. (SUU-13, -38, -42) Weapon selector knob -
RKTS & DISP/SINGLE

13. (SUU-7) Intrvl switch - SET (if required)

Note

14. Station selector button(s) - PUSH ON
a. Green light(s) - ON

15. Master arm switch - ARM
a. Amber light(s) - ON

Bomb Run

1. (P) Receiver gain - MINIMUM

2. (P) Lockon target.

3. Bomb release button - DEPRESS AND HOLD

4. (SUU-7) Amber CBU lights - MONITOR

a. Blinking light - Tubes remaining

b. Amber light out - All tubes have received a
firing pulse.

Note

The CBU lights will not monitor the empty
status of the flare dispenser, SUU-13,

SUU-38, SUU-42.

During the initial dive toward the target
area, the pilot reduces the receiver gain
to obtain a single return, depress the ac¬
tion switch to Half-Action, place the range
strobe in the center of the return, and then
depress the action switch to Full-Action
and release. After lockon, the AC places
the pipper on target, depresses and holds
the bomb release button, and initiates the
desired delivery maneuver. After the bomb
is automatically released, the pullup light
will illuminate and will go out when the
bomb button is released.

LAYDOWN

Before Bomb Run

1. Delivery mode selector knob - LAYDOWN

2. Sight mode selector knob - A/G

3. Reticle depression counter - SET (if required)

Set the IP-to-target sight setting.

4. HSI mode switches - NAV COMP

If the HSI steering information is to be used,
the NAV COMP position must be selected.

5. (P) INS mode selector knob - NAV

6. (P) WRCS target range counter - SET

Set the distance from IP to target.

7. (P) WRCS release range counter - SET
a. Range switch NORM or XI00

8. (P) WRCS release advance counter - SET
(if required)

9. Weapon selector knob - RKTS & DISP

a. (SUU-13, -38, -42) Weapon selector knob -
RKTS & DISP/SINGLE

10. (SUU-7) Intrvl switch - SET (if required)

11. Station selector button(s) - PUSH ON
a. Green light - ON

12. Master arm switch - ARM
a. Amber light - ON

Bomb Run

Approach the target at the preplanned release alti¬
tude and airspeed. When the aircraft is directly over
the IP, or when the pipper is on target, depress and
hold the bomb release button. Maintain a constant
airspeed, altitude, and course until the bomb is
automatically released. The pullup light will illumi¬
nate to indicate bomb release and will go out when
the bomb button is released. Wind corrections for
the bomb must be applied prior to depressing the
bomb button.

1. Bomb release button - DEPRESS AND HOLD

2. SUU-7 CBU lights - MONITOR

a. Blinking light - Tubes Remaining

b. Amber light out - All tubes have received a
firing pulse.

Note

The CBU lights will not monitor the empty
status of the flare dispenser, SUU-13,

SUU-38, SUU-42.

OFFSET BOM BING/TARGET FIND

Before IP

1. Delivery mode selector knob - OFFSET BOMB
or TGT FIND

2. Sight mode selector knob - A/G

The optical sight reticle is electrically caged
to the RBL and to 0° in azimuth. The roll
tabs display aircraft attitude until target in¬
sert, then steering commands to the target.

3. Navigation mode selector knob - NAV COMP

4. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

5. (P) INS mode selector knob - NAV

6. (P) BDHI mode switch - NAV COMP

7. (P) Weapon delivery panel - SET

a. Activate switch - NORMAL

b. Tgt find switch - NORMAL

c. Range switch - AS REQUIRED

8. (P) WRCS input counters - SET

a. Target distance N/S - 100-ft increments

b. Target distance E/W - 100-ft increments

c. IP altitude MSL - 100-ft increments

d. Release range - 10-ft or 100-ft increments
(Offset bomb)

e. Release advance - Milliseconds (Offset
bomb, if required)

2-74

Change 1

T.O. 1F-4C-34-1-1

9. Weapon selector knob - RKTS & DISP (Offset
bomb)

a. (SUU-13, -38, -42) Weapon selector knob -
RKTS & DISP/SINGLE

10. (SUU-7) Intrvl switch - SET (if required)

Note

The ADI will not provide steering if the
weapon selector knob is on AGM-45.

11. Station selector button(s) - PUSH ON
a. Green light - ON

12. Master arm switch - ARM
a. Amber light - ON

Bomb Run-Offset Radar IP

1. (P) Radar power - OPR

2. (P) Radar mode switch - MAP-PPI

3. (P) Antenna stab switch - NOR

4. (P) Cursor intensity - ADJUST

5. (P) Antenna elevation - ADJUST

6. (P) Scan switch - WIDE

7. (P) Radar range selector knob - R2 or R3

8. (P) Operate the along track cursor to position
the range cursor over the RIP.

9. (P) Operate the cross track cursor to position
the offset cursor over the RIP.

10. (P) Freeze button - PUSH ON

Note

• Do not position the range cursor below zero
range. If the range cursor is moved below
zero range and then moved out over the IP,
the steering information will be in error by
180° even through the cursor responds nor¬
mally to along track cursor control move¬
ments.

11. (P) Target insert button - PUSH ON

12. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

13. SUU-7 CBU lights - MONITOR

a. Blinking light - Tubes Remaining

b. Amber light out - All tubes have received a
firing pulse.

When the aircraft is on course to the target
and at a preplanned release altitude and
airspeed, depress and hold the bomb re¬
lease button until the bomb is released, as
indicated by illumination of the pullup light.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

Note

The CBU lights will not monitor the empty
status of the flare dispenser, SUU-13,
SUU-38, SUU-42.

Bomb Run-Visual IP Fly-Over

1. (P) When over IP, freeze button and target in¬
sert button - PUSH ON

2. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

3. SUU-7 CBU lights - MONITOR

a. Blinking light - Tubes Remaining

b. Amber light out - All tubes have received a
firing pulse.

When the aircraft is on course to the target
and at a preplanned release altitude and
true airspeed, depress and hold the bomb
release button until bomb release occurs,
indicated by the illumination of the pullup
light.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

POST STRIKE
Before Landing

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & stores switch - NORMAL

■4. Sight mode selector knob - STBY, or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

Armament Area (De-Arming)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

Change 1

2-75

T.O. 1F-4C-34-1-1

A/B 45-1, Y-2, Y-4 SPRAY TANK DISPENSERS [F-4E1

PREFLIGHT

| Refer to part 4, figure 2-24.

INFLIGHT

DISPENSING

1. Delivery mode selector knob - DIRECT

2. Station select - LOADED STATIONS
a. Green light - ON

3. Weapon selector knob - RKTS & DISP, SINGLE

4. Arm nose tail switch - NOSE & TAIL

5. Master arm switch - ARM
a. Amber light - ON

Note

• On the A/B 45Y-4 dry agent spray tank, en¬
ergizing the master arm switch arms the
tank. The Y-4 tank can be de-armed by po¬
sitioning the master arm switch to SAFE.

6. Bomb button - DEPRESSED

7. Amber light - MONITOR

a. Blinking amber light - spray remaining

b. Amber light out - no spray remaining

DISPENSER RELEASE

1. Wing tank jettison switch - JETT

Placing the master arm switch to ARM arms
the A/B 45Y-1 tank causing an explosive
squib to discharge, thereby pressurizing the
bladder of liquid.

WARNING

Once the A/B 45Y-1 is armed, it cannot be
de-armed and therefore must not be brought
back to base.

Note

• On the A/B 45Y-2 dry agent spray tank, en¬
ergizing the master arm switch causes the
agent container to be pressurized by ram air
for proper dissemination. The Y-2 tank can
be de-armed by positioning the master arm
switch to SAFE.

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & store switch - NORMAL

4. Sight mode selector knob - STBY, or CAGE

5. All DCU-94/A station selector switches (5)
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

TMU-28/B SPRAY TANK (F-4E)

PREFLIGHT

|Refer to part 4, figure 2-24.

INFLIGHT

1. Weapon selector knob - A/G MISSILE (Not in
RKTS & DISP)

2. Arm nose tail switch - SAFE

3. Master arm switch - SAFE

DISPENSING

1. Station selector button(s) - SELECT LOADED
STATION (S)

a. Green light(s) - ON

2. Master arm switch - ARM

a. Amber light(s) remain - OFF

3. To extend boom, weapon selector knob - RKTS
& DISP/SINGLE

a. While boom is extending, amber light(s) -
ON STEADY

b. Boom fully extended, amber light(s) -
BLINKING

4. To begin dispensing, bomb button - DEPRESS
AND HOLD (8 sec)

5. To stop dispensing, bomb button - RELEASE

6. Weapon selector knob - A/G MISSILE (Not in
RKTS & DISP)

7. To retract boom, arm nose tail switch - NOSE
& TAIL

a. Amber light continues to blink after boom is
retracted.

Note

The amber light will continue to blink until
power is removed from the aircraft, except
when the station selector button is pushed off.
When the station selector button is pushed on,
the light will begin blinking again.

8. Station selector button(s) - PUSH OFF
a. Green and amber lights - OFF

2-76

Change 1

T.O. 1F-4C-34-1-1

DISPENSER RELEASE

1. Wing tank jettison switch - JETT

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & store switch - NORMAL

4. Sight mode selector knob - STBY, or CAGE.

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

PAU-7/A SPRAY TANK (F-4E)

PREFLIGHT

| Refer to part 4, figure 2-24.

INFLIGHT

1. Weapon selector knob - A/G MISSILE (NOT
RKTS & DLSP)

2. Arm nose tail switch - SAFE

3. Master arm switch - SAFE

DISPENSING

1. Station selector buttons - RO, LO, OR BOTH
AS REQUIRED

a. Green select light(s) - ON

2. Weapon selector knob - RKTS & DISP/SINGLE

3. Bomb mode selector knob - DIRECT

4. Master arm switch - ARM

5. To extend boom, arm nose tail switch - NOSE
& TAIL

6. To dispense, bomb button - DEPRESS & HOLD
Tank will dispense with boom up or down.

7. To stop dispensing, bomb button - RELEASE

8. To retract boom, arm nose tail switch - TAIL
(90 sec)

9. Station selector button(s) - PUSH OFF (after
boom retract)
a. Green light(s) - OFF

10. Delivery mode select knob - OFF

DISPENSER RELEASE

I. Wing tank jettison switch - JETT

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select button(s) - OFF

3. Guns & store switch - NORMAL

4. Sight mode selector knob - STBY or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

SUU-16/A, -23/A GUN POD (F-4E)

PREFUGHT

| Refer to part 4, figure 2-25.

INFLIGHT

STRAFING

1. Sight mode selector knob - A/G

2. Reticle depression counter - SET

Note

• If the optical is to be used, the OFF or DI¬
RECT position should be selected on the de¬
livery mode selector panel.

• Reference to the RAT (ram air turbine) is
applicable to the SUU-16/A gun pod only.

3. Gun clear switch - NONCLEAR or AUTO CLEAR

Change 1

2-77

T.O. 1F-4C-34-1-1

4. Weapon selector knob - GUNS or AS REQUIRED

When BOMBS or RKTS & DISP are selected,
the guns and stores switch must be in guns
and stores to select the guns.

5. Guns and stores switch - NORMAL or GUNS &
STORES

When the weapon selector knob is positioned
to GUNS, the switch should be in NORMAL.

6. Station selector button(s) - PUSH LOADED
STATION(S)

a. Green light(s) - ON (SUU-23 Prestart)

7. Master arm switch - ARM

a. Amber light(s) - ON, RAT OUT (SUU-16)

The RAT will extend when the master arm
switch is placed to ARM.

8. Trigger switch - ACTUATE

AIR-TO-AIR

1. Sight mode selector knob - A/A

2. Gun clear switch - NONCLEAR or AUTO
CLEAR

3. Weapon selector knob - GUNS or AS RE¬
QUIRED

4. Guns and stores switch - NORMAL or GUNS &
STORES

5. Station selector button(s) - PUSH LOADED
STATION(S)

a. Green light(s) - ON (SUU-23 Prestart)

6. (WSO) Radar power - OUT OF OFF

7. (WSO) Radar mode switch - AS REQUIRED

8. (WSO) Radar range - R1

9. Master arm switch - ARM

a. Amber light(s) - ON, RAT OUT (SUU-16)

The RAT will extend when the master arm
switch is placed to ARM.

10. (WSO) Target lock-on - ACCOMPLISH

11. Trigger switch - ACTUATE

FINAL BURST SAFE GUNS
(Rounds Remaining)

1. Gun clear switch - AUTO CLEAR

2. Trigger switch - ACTUATE

3. Station selector button - PUSH OFF

a. Green light - OFF

b. Amber light - OFF, RAT IN (SUU-16)

The RAT will retract when the station se
lector button is pushed OFF.

4. Guns and stores switch - NORMAL

5. Master arm switch - SAFE

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. Guns & stores switch - NORMAL

4. Sight mode selector knob - STBY or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

PREFLIGHT

Refer to part 4.

EXTERIOR INSPECTION

(Not Applicable)

INFLIGHT

M61A1 NOSE GUN (F-4E)

6. Guns and stores switch - NORMAL or GUNS &
STORES

7. Nose station selector button - PUSH ON
a. Green light - ON

8. Master arm switch - ARM
a. Amber light - ON

9. Trigger switch - ACTUATE

a. Zero rounds remaining - AMBER LIGHT
OFF

STRAFING

1. Sight mode selector knob - A/G

2. Reticle depression counter - SET

Note

With the sight in the A/G mode, the OFF or
DIRECT position should be selected on the
delivery mode selector panel.

3. Rounds counter - SET

| 4. Rate switch - HIGH or LOW

5. Weapon selector knob - GUNS or AS RE¬
QUIRED

When BOMBS or RKTS & DISP are selected,
the guns and stores switch must be in GUNS
& STORES to select the guns.

AIR-TO-AIR

1. Sight mode selector knob - A/A

2. Rounds counter - SET

3. Rate switch - HIGH or LOW

4. Weapon selector knob - GUNS

5. Station selector button(s) - PUSH ON
a. Green light - ON

6. (WSO) Radar power - OPR

7. (WSO) Radar mode switch - AS REQUIRED

8. (WSO) Radar range - AS REQUIRED

9. Master arm switch - ARM
a. Amber light - ON

10. (WSO) Target lock-on - ACCOMPLISH

11. Trigger switch - ACTUATE

a. Zero rounds remaining - AMBER LIGHT
OFF

2-78

Change 5

T.O. 1F-4C-34-1-1

SAFE GUNS

1. Nose station selector button - PUSH OFF

a. Green light - OFF

b. Amber light - OFF

2. Master arm switch - SAFE

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & stores sw - NORMAL

4. Sight mode selector knob - STBY or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

AGM-12B/C/E MISSILE |F-4E)

PREFLIGHT

I Refer to part 4, Cockpit Weapons Check and Exterior
Inspection (AGM-12B/C/E Missiles)

INFLIGHT

TRANSMITTER CHECK

Perform an airborne check as follows:

1. Delivery mode select knob - DIRECT

2. Station selector buttons - OFF
a. Green lights - OFF

3. Warning lights test sw - TEST

a. Station green and amber lights - ON

4. Weapon selector knob - AGM-12

5. Master arm switch - ARM

a. All station amber lights - OFF

6. Bomb button - DEPRESS

7. Control handle - TRANSMIT COMMANDS

The transmitter timer is energized for 50 ±
10 seconds.

8. Master arm switch - SAFE

BEFORE MISSILE LAUNCH

1. (ACP) Oxygen diluter selector - 100 PER¬
CENT

2. Weapon selector knob - AGM-12

3. Station selector button - DEPRESS
a. Green light - ON

Change 3

2-79

T.O 1F-4C-34-1-1

MISSILE LAUNCH

1. Master arm switch - ARM
a. Station amber light - ON

2. Bomb button - DEPRESS (2 sec approx)

Depress and hold the bomb button until the
missile fires or until the launch is aborted
due to missile malfunction.

To immediately arm a second missile for re-attack:

3. Station selector button (just fired) - DEPRESS
j Green light - OFF

4. ;> ation selector button (next missile) - DE¬
PRESS

a. Green light - ON

b. Amber light - ON

MISSILE FLIGHT (AGM-12E)

To prevent AGM-12E warhead from functioning

1. (WSO) Armament power circuit breaker -
PULL (6B, No. 1 panel)

If it is necessary to safe the missile, pull
circuit breaker 6B.

AFTER MISSILE ATTACK

1. Armament switches - OFF/SAFE

a. Master arm switch - SAFE

b. Station selector buttons - OFF

2. Emergency vent handle - CYCLE

Pull to de-pressurize, then push to pres¬
surize to cycle cockpit air in case of contain
ination by missile exhaust gases.

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & stores switch - NORMAL

4. Sight mode selector knob - STBY, or CAGE

5. All DCU-94/A station select switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

SUU-20 BOMB/ROCKET DISPENSERSJF-4E)

PREFLIGHT

| Refer to part 4.

INFLIGHT

ROCKET DELIVERY

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Intrvl switch - .10 OR .14 ONLY

5. Station select - AS REQUIRED
a. Green light - ON

6. Weapon selector knob - RKTS & DISP

7. Master arm switch - ARM
a. Amber light - ON

BOMB DELIVERY

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - AS REQUIRED

4. Intrvl switch - .10 OR .14

5. Station select - AS REQUIRED
a. Green light - ON

6. Weapon selector knob - BOMBS/SINGLE/RIP¬
PLE/TRIPLE

7. Master arm switch - ARM
a. Amber light - ON

Note

* There is no cockpit indication to determine
that all bombs or rockets have been released
or fired.

* The intervalometers within the SUU-20 can¬
not be rehomed in flight for an attempt to re¬
lease or fire a hung bomb or rocket.

* Do not use an aircraft interval setting of 0.06

BEFORE LANDING

1. Master arm switch - SAFE

2. Station selector knob - OFF

3. Guns & stores switch - NORMAL

4. Sight mode selector knob - STBY or CAGE

5. All DCU-94/A station selector switches (5)
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

2-80

Change 6

T.O. 1F-4C-34-1-1

SUU-21/A BOMB DISPENSER (F-4E)

PREFLIGHT

Refer to part 4, cockpit weapons check and Exterior
Inspection (SUU-21/A)

INTERIOR INSPECTION (DCU-94/A)

Before applying external power:

1. All station selector switches (5) - AFT

2. Station select switch guard - INSTALLED

If other munitions are aboard, the required
guard should be installed.

3. Master release lock switch - AFT

4. Option selector knob - OFF

5. Bomb mode select knob - OFF

6. (P) Nuclear store consent switch - SAFE

With the dispenser doors open, proceed as follows:

7. External power - APPLY

8. Generator switches - EXT ON

9. Lamp test button - PRESS

a. Warn and unlocked lights - ON

10. Option selector knob - SAFE

a. Loaded station warn light (s) - FLASHING
(doors closing)

b. Loaded station warn light(s) - OFF (doors
closed)

11. Option selector knob - OFF

INFLIGHT

ON BOMB RANGE (DCU-94/A)

1. Option selector knob - SAFE

2. Loaded station selector switch - FORWARD
a. Loaded station WARN light - ON

3. (P) Nuclear store consent switch - REL/ARM
a. Loaded station WARN light - OFF

4. Option selector knob - GRD

a. Loaded station WARN light - FLASHING
(doors opening)

b. Loaded station WARN light - ON (doors
open)

5. Delivery mode selector knob - AS REQUIRED

6. Weapon selector knob - NOT RKTS & DISP

Note

When the SUU-21/A dispenser is loaded on
the inboard stations, bomb release will not
occur if the weapon selector knob is on
RKTS & DISP.

BEFORE BOMB RUN (DCU-94/A)

1. Master release lock switch - FORWARD
a. Loaded station UNLOCKED light - ON

2. Loaded station WARN light - ON

AFTER BOMB RELEASE (DCU-94/A)

Manual Operation

After each bomb release, the dispenser doors re¬
main open and additional switching procedures are

unnecessary. With the DIRECT bombing mode se¬
lected, the release system (pickle button) is hot. If
it is necessary to safe the system between runs,
place the master release lock switch AFT, and re¬
select FWD just prior to the next run.

Automatic Operation

1. At bomb release loaded station WARN light -
FLASHING

2. Loaded station WARN light - OFF (doors
closed)

3. Option selector knob - SAFE

4. Option selector knob - GRD

a. Loaded station WARN light - FLASHING

b. Loaded station WARN light - ON (doors open)

AFTER FINAL BOMB RELEASE (DCU-94/A)

1. (Auto mode) Loaded station WARN light -
FLASHING

2. (Auto mode) Loaded station WARN light - OFF
(doors closed)

3. Option selector knob - SAFE

a. (Man. mode) Loaded station WARN light -
FLASHING

b. (Man. mode) Loaded station WARN light -
OFF (doors closed)

4. Master release lock switch - AFT

a. Loaded station UNLOCKED light - OFF

5. Delivery mode selector knob - OFF

WARNING

If the dispenser doors do not close and all
bombs have not been expended, the aircraft
must be flown to avoid populated areas to the
greatest degree practicable.

AFTER LANDING (DCU-94/A)

To open dispenser doors, if required:

1. (P) Nuclear store consent switch - REL/ARM

2. Loaded station selector switch - FORWARD

3. Option selector knob - GRD

a. Loaded station WARN light - FLASHING

b. Loaded station WARN light - ON (doors open)

4. All electrical power - REMOVED

Note

All electrical power must be removed from
the aircraft before performing steps 5, 6 and
7 to preclude the dispenser doors from clos¬
ing.

5. Option selector knob - OFF

6. All station selector switches (5) - AFT

7. (P) Nuclear store consent switch - SAFE

Change 4

2-81

T.O. 1F-4C-34-1-1

SUU-21/A BOMB DISPENSER (MODIFIED!

PREFLIGHT

These procedures consider the employment of SUU-
21/A dispensers modified for use with pedestal panel
controls and inboard (stations 2 and 8) carriage only.

Refer to part 4, Cockpit Weapons Check and Ex¬
terior Inspection (SUU-21/A Dispenser).

INTERIOR INSPECTION

If the dispenser doors are open, close the doors as
follows:

1. External power - APPLY

2. Generator switches - EXT ON

3. Armament safety override - DEPRESS

4. Station select button (s) - DEPRESS
a. Station green light(s) - ON

5. Master arm switch - ARM

a. Station amber light(s) - ON

6. Arm nose tail switch - NOSE

a. Station amber light(s) - FLASHING (doors
closing)

b. Station amber light(s) - OFF (doors closed)

7. Station select buttons(s) - OFF

8. Master arm switch - SAFE

WEAPON RELEASE

1. Optical sight - SET

a. Mode selector - A/G

b. Reticle depression knob - SET AS REQUIRED

2. Delivery mode selector knob - AS REQUIRED

3. Weapon selector knob - BOMBS

4. Station select button(s) - DEPRESS

5. Master arm switch - ARM
a. Amber light(s) - ON

6. Arm nose tail switch - NOSE & TAIL

a. Station amber light - FLASHING (doors
opening)

b. Station amber light - ON (doors open)

7. Bomb button - DEPRESS

AFTER FINAL BOMB RELEASE

1. Arm nose tail switch - NOSE

a. Station amber light - FLASHING (doors
closing)

b. Station amber light - OUT (doors closed)

2. Master arm switch - SAFE

3. Station select - OFF

4. Delivery mode selector knob - OFF

5. Sight mode selector knob - STBY or CAGE

AFTER LANDING

To Open SUU-21/A Dispenser Doors:

1. Armament safety override button - DEPRESS

2. Station select button(s) - DEPRESS

3. Master arm switch - ON

4. Arm nose tail switch - NOSE & TAIL

a. Station amber light (s) - FLASHING (doors
opening)

b. Station amber light (s) - ON (doors open)

5. Station select button(s) - OFF

6. Master arm switch - OFF

MODIFIED A/A 37U-15 TOW TARGET SYSTEM |F-4E|

PREFLIGHT

Refer to part 4, figure 2-29.

INFLIGHT

PRE-TAKEOFF

To reduce rolling tendencies immediately after take¬
off, the following aileron trim positions are recom¬
mended. Trim settings are the same with or without
centerline tank.

a. Dart system on station 1, station 9 empty: 2.5
inches left aileron down (trim 2.5 seconds to right of
neutral), 1.5 inches right rudder (trim 1.5 seconds to
right of neutral).

b. Dart system or station 1, external fuel tank on
station 9: 3.5 inches right aileron down (trim 3.5
seconds to left of neutral), 1.0 Inch left rudder (trim
1.0 seconds to left of neutral).

Note

The tow target system, carried on the left
outboard wing station, may induce 20° to 30°
errors in the remote compass transmitter.
Due to this effect, the DG mode on the com¬
pass controller should be selected.

TAKEOFF

Initiate a slow pitch rotation at 140 KLAS to obtain 8°
pitch attitude indicated on the ADI for liftoff at 180 to
190 KLAS. Decrease thrust after gear and flap re¬
traction to ensure that 275 KLAS is not exceeded.

Note

Refer to T.O. 1F-4C-1 External Store Limita¬
tions for A/A 37U-15 Tow Target System in¬
flight limitations.

2-82

Change 4

T.O. 1F-4C-34-1-1

TARGET DEPLOYMENT

I 1. Select DG mode on compass controller.

2. Delivery mode selector knob - DIRECT

3. Weapon selector knob - BOMBS-SINGLE

4. Station select - LO
a. Green light - ON

5. Arm nose tail switch - SAFE

6. Master arm switch - ARM
a. Amber light - ON

7. Bomb Button - DEPRESSED

Depressing the bomb button deploys the tar
get.

CAUTION I

Do not attempt to deploy a damaged dart tar¬
get. Motion of the damaged target after re¬
lease is unpredictable. Possible contact with
the aircraft could be hazardous.

8. Master arm switch - SAFE
a. Amber light - OFF

CABLE CUT

1. Master arm switch - ARM
a. Amber light - ON

2. Tow cable - CUT

a. (before Rev K) Bomb button - DEPRESS

b. (after Rev K) Arm nose tail switch - NOSE

3, Chase plane, acknowledge cable cut.

Emergency Cut

1. Arm nose tail sw - NOSE & TAIL or TAIL

2. Chase plane, acknowledge cable cut.

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & store switch - NORMAL

4. Sight mode selector knob - STBY or CAGE

5. All DCU-94/A station selector switches (5) -
AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

LANDING WITH STOWED TARGET (DAMAGED
OR UNDAMAGED)

1. Flaps - 1/2

2. Angle of attack - 17 to 18 UNITS

(With wing tank use less than 17 units.)

INFLIGHT PROCEDURES FOR BOMBING
RANGE SELECTED WEAPONS (F-4E)

INFLIGHT

ROCKET LAUNCHERS AND SUU-20

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Intrvl switch - . 10 OR . 14 ONLY

5. Station select - AS REQUIRED
a. Green light - ON

6. Weapon selector knob - RKTS & DISP

7. Master arm switch - ARM
a. Amber light - ON

BOMBS,SUU-20

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - AS REQUIRED

4. Intrvl switch - . 10 OR . 14

5. Station select - AS REQUIRED
a. Green light - ON

6. Weapon selector knob - BOMBS/SINGLE/
RIPPLE/TRIPLE

7. Master arm switch - ARM
a. Amber light - ON

BOMBS,SUU-21/A (DCU-94/A)

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - AS REQUIRED

4. Weapon selector knob - BOMBS

5. Option selector knob - SAFE

6. Loaded station selector switch - FORWARD
a. Warn light - ON

7. (WSO) Nuclear consent switch- REL/ARM
a. Warn light - OFF

8. Option selector knob - GRD

a. WARN light - FLASH

b. WARN light - ON

9. Master release lock switch - FORWARD
a. UNLOCKED light - ON

Note

To reopen doors during automatic operation,
repeat steps 5 and 8.

Change 7

2-83

T.O. 1F-4C-34-1-1

AFTER FINAL RELEASE (DCU-94/A) To Close Doors

1. Option selector knob - SAFE
a. WARN light - FLASH/OFF

2. Master release lock switch - AFT
a. UNLOCKED light - OFF

3. Loaded station selector switch - AFT

4. (WSO) Nuclear consent switch - SAFE

BOMBS - SUU-21/A MODIFIED

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - AS REQUIRED

4. Weapon selector knob - BOMBS

5. Station select button(s) - DEPRESS

6. Master arm switch - ARM
a. Amber light (s) - ON

7. Arm nose tail switch - NOSE & TAIL

a. Station amber light(s) - FLASHING (doors
opening)

b. Station amber light(s) - ON (doors open)

1. Arm nose tail switch - NOSE

a. Amber light - FLASHING, THEN OFF

STRAFE • SUU-16/A, 23/A, and M61A NOSE GUN

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - OFF/DIRECT

4. Station select - AS REQUIRED
a. Green light - ON

5. Weapon selector knob - GUNS/AS REQUIRED

6. Gun clear switch - AS REQUIRED

7. Guns and stores switch - AS REQUIRED

8. Master arm switch - ARM
a. Amber light - ON

RANGE DEPARTURE

1. Sight mode selector knob - CAGED, STBY

2. Delivery mode selector knob - OFF

3. Station select - OFF

4. Master arm switch - SAFE

2-84

Change 5

" Figures 2-16 thru 2-20 deleted."

T.O. 1F-4C-34-1-1

BOMBS & SUU-20 |F-4E) AFTER T.O. 1F-4E-556

PREFLIGHT

Refer to part 4.

INFLIGHT

Note

• There is no cockpit indication to determine
that all bombs or rockets have been released
or fired from SUU-20 bomb/rocket dispenser.
The intervalometers within the SUU-20 can¬
not be rehomed in flight for an attempt to re¬
lease or fire a hung bomb or rocket. Do not
use an aircraft interval setting of less than
0.100 second when using the SUU-20.

•After T.O. 1F-4-750 (BRU-5/A centerline
rack), the following release procedures may
be used to release the Ml 18 or MK 84 GP
bombs from the CL station. On unmodified
aircraft the DCU-94/A procedures may be
used.

DIRECT DELIVERY MODE
Bomb Release-Armed

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Weapon selector - BOMBS

5. AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

I 6. Arm nose tail switch - (ON) AS REQUIRED

7. Station select - LOADED STATION(S)
a. Green light (s) - ON

8. Master arm switch - ARM

a. Heads up ARM light - ON

b. Station ARM light(s) - ON

Note

With the weapon selector in BOMBS, the
station ARM (amber) light illuminates only
if the arm/nose tail switch is in one of the
ON (armed) positions.

9. Bomb button - DEPRESS

a. Pullup light - ON

b. When station is empty, station ARM light -
OFF

Emergency Bomb Release-Armed

1. AWRU Qty knob - C or S

[^CAUTIOn I

When selecting either C or S, observe mini¬
mum release interval between bombs re¬
leased from the same aircraft station.

2. Repeat above steps 5 thru 9, hold bomb button
depressed 4 seconds.

If all bombs do not release:

3. Weapon selector knob - RKTS & DISP

4. Weapon selector knob - BOMBS

5. Bomb button - DEPRESS (hold 4 seconds)

DIVE TOSS/DIVE LAYDOWN
Before Bomb Run

1. Delivery mode selector knob - DIVE TOSS or
DIVE LAY

2. Sight mode selector knob - A/G

The sight reticle is electrically caged to the
radar boresight line ?nd is drift stabilized.

3. HSI mode switches - NAV COMP

If the HSI indications are to be used, the
NAV COMP position must be selected.

4. (WSO) INS mode selector knob - NAV

5. (WSO) Radar mode - AIR-GND

6. (WSO) Radar range - R1 or R2

7. (WSO) Radar power - OPR

B-sweep, acquisition symbol, and el strobe
centered on scope.

8. (WSO) Antenna stab switch - NOR

9. (WSO) WRCS drag coefficient counter - SET
(Dive Toss Only)

10. (WSO) WRCS release range counter - SET
(Dive Lay Only)

a. Range switch - NORM or XI00

11. (WSO) WRCS release advance - SET (if re¬
quired)

12. Weapon selector knob - BOMBS

13. AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

14. Arm nose tail switch - (ON) AS REQUIRED

15. Station select - LOADED STATION(S)
a. Green light (s) - ON

16. Master arm switch - ARM

a. Heads up ARM light - ON

b. Station ARM light (s) - ON

Not*

• With the weapon selector in BOMBS, the
station ARM (amber) light illuminates only
if the arm/nose tail switch is in one of the
ON (armed) positions.

* The optical sight and the radar antenna are
drift stabilized. Additional upwind correction
must be made for the wind effect on the high
drag bombs. Wind correction is not re¬
quired for the low drag bombs (M117 etc.).

Bomb Run

1. (WSO) Receiver gain - MINIMUM

2. (WSO) Lockon target (CALL)

Change 6

2-85

T.O. 1F-4C-34-1-1

3. Bomb release button - DEPRESS AND HOLD

a. After bomb release, pullup light - ON

b. After station is empty, station ARM light -
OFF

During the initial dive toward the target
area, the WSO reduces the receiver gain
to obtain a single return, depress the ac¬
tion switch to Half Action, place the range
strobe in the center of the return, and then
depress the action switch to Full Action
and release. After lockon, the AC places
the pipper on target, depresses and holds
the bomb release button, and initiates the
desired delivery maneuver. After the bomb
is automatically released, the pullup light
wiU illuminate and will go out when the
bomb button is released. The station
ARM light will go out when the station is
empty.

LAYDOWN

Before Bomb Run

1. Delivery mode selector knob - LAYDOWN

2. Sight mode selector knob - A/G

3. Reticle depression knob - SET (if required)

Set the IP-to-target sight setting.

4. HSI mode switches - NAV COMP

If the HSI steering information is to be used,
the NAV COMP position must be selected.

5. (WSO) INS mode selector knob - NAV

6. (WSO) WRCS target range counter - SET

Set the distance from IP to target.

7. (WSO) WRCS release range counter - SET

a. Range switch - NORM or XI00

8. (WSO) WRCS release advance counter - SET
(if required)

9. Weapon selector knob - BOMBS

10. AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

| 11. Arm nose tail switch - (ON) AS REQUIRED

12. Station select - LOADED STATION(S)
a. Green light(s) - ON

13. Master arm switch - ARM

a. Heads up ARM light - ON

b. Station ARM light(s) - ON

Note

I With the weapon selector in BOMBS, the
station ARM (amber) light illuminates only
if the arm/nose tail switch is in one of the
ON (armed) positions.

Bomb Run

automatically released. The pullup light will illumi¬
nate to indicate bomb release and will go out when
the bomb button is released. Wind corrections for
the bomb must be applied prior to depressing the
bomb button.

1. Bomb release button - DEPRESS AND HOLD

a. At bomb release, pullup light - ON

b. When a station is empty, station ARM light -
OFF

OFFSET BOMBING/TARGET FIND
Before IP

1. Delivery mode selector knob - OFFSET BOMB
or TGT FIND

2. Sight mode selector knob - A/G

The optical sight reticle is electrically caged
to the RBL and to 0° in azimuth. The roll
tabs display aircraft attitude until target in¬
sert, then steering commands to the target.

3. Navigation mode selector knob - NAV COMP

4. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

5. (WSO) INS mode selector knob - NAV

6. (WSO) BDHI mode switch - NAV COMP

7. (WSO) Weapon delivery panel - SET

a. Activate switch - NORMAL

b. Tgt Find switch - NORMAL

c. Range switch - AS REQUIRED

Note

The position of the range switch will affect
the value placed in the release RANGE read¬
out: times 10 (NORMAL), or times 100.

8. (WSO) WRCS input counters - SET

a. Target distance N/S - 100-ft increments.

b. Target distance E/W - 100-ft increments.

c. IP altitude MSL - 100-ft increments.

d. Release range - 10-ft or 100-ft increments

(Offset bomb)

e. Release advance - Milliseconds (Offset
bomb, if required)

9. Weapon selector knob - BOMBS (Offset bomb)

Note

The ADI will not provide steering if the
weapon selector knob is on ARM.

10. AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

11. Arm nose tail switch - (ON) AS REQUIRED |

12. Station select - LOADED STATION (S)
a. Green light(s) - ON

13. Master arm switch - ARM

a. Heads up ARM light - ON

b. Station ARM light (s) - ON

2-86

Change 6

T.O. 1F-4C-34-1-1

Note

With the weapon selector in BOMBS, the
station ARM (amber) light illuminates only
if the arm/nose tail switch is in one of the
ON (armed) positions.

Bomb Run-Offset Radar IP

1. (WSO) Radar power - OPR

2. (WSO) Radar mode - MAP-PPI

3. (WSO) Antenna stab switch - NOR

4. (WSO) Cursor intensity - ADJUST

5. (WSO) Antenna elevation - ADJUST

6. (WSO) Scan switch - WIDE

7. (WSO) Radar range - R2 or R3

8. (WSO) Operate the along track cursor to posi¬
tion the range cursor over the RIP

9. (WSO) Operate the cross track cursor to po¬
sition the offset cursor over the RIP.

10. (WSO) Freeze button - PUSH ON

Note

11. (WSO) Target insert button - PUSH ON

12. Bomb release button - DEPRESS AND HOLD

(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, station ARM light -
OFF

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

Bomb Run-Visual IP Fly-Over

1. (WSO) When over IP, freeze button and target
insert button - PUSH ON

When the aircraft is directly over the IP, the
freeze button and the target insert button are
pushed ON simultaneously. The steering in¬
struments supply steering commands to the
target, and the cursors start tracking the
target. If the target is visible on the scope,
the WSO may touch-up the cursors when the
target elevation is set in the ALT RANGE
control.

2. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, station ARM light -
OFF

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

LABS/OFFSET BOAAB/TGT FIND
After Takeoff

1. Delivery mode selector knob - OFFSET BOMB
or TGT FIND

2. (WSO) Target find switch - HOLD

Select HOLD on the weapon delivery panel.

3. Sight mode selector knob - A/G

The optical sight reticle is electrically caged
to the RBL and to 0° in azimuth. The roll
tabs display aircraft attitude until target in¬
sert, then steering commands to the target.

4. Navigation mode selector knob - NAV COMP

5. HSI mode switches - NAV COMP

If the HSI indications are to be used, the NAV
COMP position must be selected.

6. (WSO) INS mode selector knob - NAV

7. (WSO) BDHI mode switch - NAV COMP

8. (WSO) WRCS input counters - SET

a. Target distance N/S - 100-ft increments

b. Target distance E/W - 100-ft increments

c. IP altitude MSL - 100-ft increments

d. Release range - 10-ft or 100-ft increments
(Offset bomb)

e. Release range - LABS pullup range, 10-ft
or 100-ft increments

Note

The X100 factor is selected through the
range switch on the weapon delivery panel.

f. Release advance - Milliseconds (Offset
bomb, if required)

9. Weapon selector knob - BOMBS (Offset bomb)

Change 6

2-87

T.O. 1F-4C-34-1-1

Note

The ADI will not provide steering if the
weapon selector knob is on AGM-45.

10. AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

| 11. Arm nose tail switch - (ON) AS REQUIRED

12. Station select - LOADED STATION(S).
a. Green light (s) - ON

13. Master arm switch - ARM

a. Heads up ARM light - ON.

b. Station ARM light(s) - ON

Note

I With the weapon selector in BOMBS, the
station ARM (amber) light illuminates only
if the arm/nose tail switch is in one of the
ON (armed) positions.

14. (WSO) Dual timers - SET

a. Pullup timer - Tj

b. Release timer - T 2

15. (WSO) Release gyro - SET
a. Low angle (LOFT) - DEG

Before Bomb Run

1. (WSO) Radar power - OPR

2. (WSO) Radar mode - MAP PPI

3. (WSO) Antenna stab switch - NOR

4. (WSO) Cursor intensity - ADJUST

5. (WSO) Antenna elevation - ADJUST

6. (WSO) Scan switch - WIDE

7. (WSO) Radar range - R2 or R3

Bomb Run-Offset Radar IP

1. (WSO) Operate the along track control to posi¬
tion the range cursor over the RIP.

2. (WSO) Operate the cross track control to posi¬
tion the offset cursor over the RIP.

3. (WSO) Freeze button - PUSH ON

Note

4. (WSO) Target insert button - PUSH ON

The steering instruments display steering
commands when the target insert button is

pushed ON, and the cursor intersection will
position over the target location and track the
target. If the target is on the scope, set the
target elevation on the ALT RANGE counter
and touch-up the cursors over the target.

5. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, station ARM
light - OFF

When the aircraft is on course to the target
and at the preplanned release altitude and
airspeed, depress and hold the bomb release
button until the bomb is released, as indicated
by illumination of the pullup light.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

Bomb Run Visual IP Fly-Over

1. (WSO) When over IP, freeze button and target
insert button - PUSH ON

When the aircraft is directly over the IP, the
freeze button and the target insert button are
pushed ON simultaneously. The steering in¬
struments supply steering commands to the
target, and the cursors start tracking the
target. If the target is visible on the scope,
the WSO may touch-up the cursors when the
target elevation is set in the ALT RANGE
control.

2. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

a. At bomb release, pullup light - ON

b. When a station is empty, station ARM
light - OFF

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

Bomb Run LABS/TGT Find

1. Delivery mode selector knob (LABS) - AS
REQUIRED

Select the planned delivery mode.

Note

With the TGT find switch on HOLD, the de¬
livery mode selector may be positioned to any
LABS mode without losing WRCS function.

2. (WSO) Along track and cross track controls -
AS REQUIRED (Visual or Radar IP)

2-88

Change 6

T.O. 1F-4C-34-1-1

3. (WSO) Freeze control - PUSH ON

4. (WSO) Target Insert control - PUSH ON

5. (WSO) After target insert, activate switch -
ON

Select the ON position only after steering
instruments have transitioned to target.

6. At warning tone (Ti start) - MIL POWER
PULLUP

7. Bomb button - DEPRESS AND HOLD

LOFT BOMBING-RIPPLE RELEASE
Before Bomb Run

1. (WSO) Activate switch - NORMAL

When the WRCS is not used with the LABS
modes, the target find switch and/or the
activate switch on the weapons delivery panel
must be positioned to NORMAL.

2. (WSO) Low angle knob - SET

3. (WSO) Pull up timer - SET

4. (WSO) Release timer - SET ZERO

5. Delivery mode selector knob - LOFT

6. Weapon selector knob - BOMBS

7. AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

I 8. Arm nose tail switch - (ON) AS REQUIRED
9. Station select - LOADED STATION(S).

a. Green light(s) - ON
10. Master arm switch - ARM

a. Heads up ARM light - ON

b. Station ARM light(s) - ON

Note

I With the weapon selector in BOMBS, the sta¬
tion ARM (amber) light illuminates only if the
arm/nose tail switch is in one of the ON
(armed) positions.

AT IP

1. Bomb button - DEPRESS AND HOLD

The bomb button must be energized until the
final bomb is released.

2. At pullup point, throttles - FULL MIL POWER

Loft Bomb Delivery

Since the sight reticle is pitch stabilized, it will not
be in view above loft angles of 20°. When the air¬
craft attitude is at the preselected release angle, the

pullup light and the reticle light illuminate, and the
bombs will begin releasing in a ripple sequence.

After the final bomb is released, the bomb button is
released and the AC initiates a wingover escape ma¬
neuver to achieve a 120° turn while diving toward
minimum escape altitude. When the bomb button is
released, the pullup light will go out and the hori¬
zontal pointer will move out of view.

After Escape Maneuver

1. Master arm switch - SAFE

2. Station select (5) - OFF

3. Delivery mode selector knob - OFF

Placing the delivery mode selector knob to
OFF removes power from the bombing
timers.

CENTERLINE WEAPON RELEASE (DCU-94/A)

Before Bomb Run

1. Delivery mode selector knob - DIRECT or AS
REQUIRED

2. Optical sight - SET (if required)

3. (WSO) Nuclear store consent switch - REL/

ARM

4. DCU-94/A CL station selector switch - FOR¬
WARD

5. Arm nose tail switch - (ON) AS REQUIRED |

Bomb Run

1. DCU-94/A master release lock switch - FOR¬
WARD

a. CL UNLOCKED light - ON

2. Master arm switch - ARM
a. Heads up ARM light - ON

The master arm switch allows power to the
arm nose tail switch.

3. Delivery maneuver - EXECUTE

If the DIRECT delivery mode is selected, the
bomb is released when the bomb button is
depressed.

Note

If the bomb does not release, recheck switch
positions, select the DIRECT release mode
and depress bomb button, or energize the
nuclear store jettison control.

POST STRIKE

Before Landing

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) - AFT

7. Sight mode selector knob - STBY or CAGE

Armament Area (De-Arming)

1. Armament switches - OFF/SAFE/NORMAL

2. Aircrew - HANDS IN VIEW

Change 6

2-89

T.O. 1F-4C-34-1-1

ROCKETS & SUU-20IF-4E) AFTER T.O. 1F-4E-556

PREFLIGHT

Refer to part 4.

INFLIGHT

Note

There is no cockpit indication to determine
that all bombs or rockets have been released
or fired from SUU-20 bomb/rocket dispenser.
The intervalometers within the SUU-20 can¬
not be rehomed in flight for an attempt to re¬
lease or fire a hung bomb or rocket. Do not
use an aircraft interval setting of less than
0.100 second when using the SUU-20.

ROCKET FIRING

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Weapon selector knob - RKTS & DISP or A

5. With RKTS & DISP selected, AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

6. Station select - LOADED STATION(S)
a. Green light(s) - ON

7. Master arm switch - ARM

a. Heads up ARM light - ON

b. Station ARM light(s) - ON

8. Bomb button - DEPRESS

3. AWRU - SET

a. Intrvl controls - SET

b. Qty knob - C or S

4. Arm nose tail switch - NOT IN SAFE

With weapon selector knob in BOMBS, the
arm nose tail switch must be out of SAFE
to obtain the station ARM light on.

5. Station select - LOADED STATION(S)
a. Green light(s) - ON

6. Master arm switch - ARM

a. Heads up ARM light - ON

b. Station ARM light(s) - ON

7. Bomb button - DEPRESS (hold 4 seconds)

a. Pullup light - ON

b. When station is empty, station ARM light
OFF

If all launchers do not release:

8. Weapon selector knob - RKTS & DISP

9. Weapon selector knob - BOMBS

10. Bomb button - DEPRESS (hold 4 seconds)

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) -
AFT

7. Sight mode selector knob - STBY or CAGE

LAUNCHER RELEASE (EXCEPT SUU-20)

1. Delivery mode selector knob - DIRECT

2. Weapon selector knob - BOMBS

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF/SAFE/NORMAL

2. Aircrew - HANDS IN VIEW

CBU AND FLARE DISPENSERS IF-4EI AFTER T.O. 1F-4E-556

PREFLIGHT

Refer to part 4.

INFLIGHT

DIRECT DELIVERY MODE
Dispensing

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Weapon selector knob - RKTS & DISP or A

5. With RKTS & DISP selected, AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

6. Station select - LOADED STATION(S)
a. Green light(s) - ON

7. Master arm switch - ARM

a. Station ARM light(s) - ON

b. Heads up ARM light - ON

8. Bomb button - DEPRESS AND HOLD AS
REQUIRED

9. (SUU-7) Station ARM lights - MONITOR

a. Blinking light - Tubes Remaining

b. Station ARM light out - All tubes have
received a firing pulse.

2-90

Change 6

T.O. 1F-4C-34-1-1

Note

The Station ARM lights will not monitor the
empty status of the flare dispenser, SUU-38,
SUU-42. The station ARM light normally
goes out when all SUU-13's on that station
have timed out.

Dispenser Release

1. Delivery mode selector knob - DIRECT

2. Weapon selector knob - BOMBS

3. AWRU - SET

a. Intrvl controls - SET

b. Qty knob - C or S

4. Arm nose tail switch - NOT IN SAFE

With weapon selector knob in BOMBS, the
arm nose tail switch must be out of SAFE
to obtain the station ARM light on.

5. Station select - LOADED STATION(S)
a. Green light(s) - ON

6. Master arm switch - ARM

a. Heads up ARM light - ON

b. Station ARM light(s) - ON

7. Bomb button - DEPRESS (hold 4 seconds)

a. Pullup light - ON

b. When station is empty, station ARM light -
OFF

If all dispensers do not release:

8. Weapon selector knob - RKTS & DISP

9. Weapon selector knob - BOMBS

10. Bomb button - DEPRESS (hold 4 seconds)

DIVE LAYDOWN
Before Bomb Run

1. Delivery mode selector knob - DIVE LAY

2. Sight mode selector knob - A/G

The sight reticle is electrically caged to the
radar boresight line and is drift stabilized.

3. HSI mode switches - NAV COMP

If the HSI indications are to be used, the
NAV COMP position must be selected.

4. (WSO) INS mode selector knob - NAV

5. (WSO) Radar mode - AIR-GND

6. (WSO) Radar range - Rl or R2

7. (WSO) Radar power - OPR

B-sweep, acquisition symbol, and el strobe
centered on scope.

8. (WSO) Antenna stab switch - NOR

9. (WSO) WRCS release range counter - SET
a. Range switch - NORM or X100

10. (WSO) WRCS release advance - SET (if re¬
quired)

11. Weapon selector knob - RKTS & DISP or A

12. With RKTS & DISP selected, AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

13. Station select - LOADED STATION(S)
a. Green light(s) - ON

14. Master arm switch -ARM

a. Station ARM light(s) - ON

b. Heads up ARM light - ON

Bomb Run

Note

The optical sight and the radar antenna are
drift stabilized. Upwind correction must be
made for the wind effect on the high drag
bombs. Wind correction is not required for
the low drag bombs (Ml 17, MK 82 LDGP,
etc.).

1. (WSO) Receiver gain - MINIMUM

2. (WSO) Lockon target

3. Bomb release button - DEPRESS AND HOLD

4. (SUU-7) Station ARM lights - MONITOR

a. Blinking light - Tubes remaining

b. Station ARM light out - All tubes have
received a firing pulse.

Note

• The station ARM lights do not monitor the
empty status of the flare dispenser SUU-38,
SUU-42. The station ARM light normally
goes out when all SUU-13's on that station
have timed out.

• During the initial dive toward the target
area, the WSO reduces the receiver gain
to obtain a single return, depress the ac¬
tion switch to Half-Action, place the range
strobe in the center of the return, and then
depress the action switch to Full-Action
and release. After lockon, the AC places
the pipper on target, depresses and holds
the bomb release button, and initiates the
desired delivery maneuver. After the bomb
is automatically released, the pullup light
will illuminate and will go out when the
bomb button is released.

LAYDOWN

Before Bomb Run

1. Delivery mode selector knob - LAYDOWN

2. Sight mode selector knob - A/G

3. Reticle depression knob - SET (if required)

Set the IP-to-target sight setting.

4. HSI mode switches - NAV COMP

If the HSI steering information is to be used,

the NAV COMP position must be selected.

5. (WSO) INS mode selector knob - NAV

6. (WSO) WRCS target range counter - SET

Set the distance from IP to target.

7. (WSO) WRCS release range counter - SET
a. Range switch NORM or X100

8. (WSO) WRCS release advance counter - SET
(if required)

9. Weapon selector knob - RKTS & DISP or A

10. With RKTS & DISP selected, AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

11. Station select - LOADED STATION(S)
a. Green light(s) - ON

12. Master arm switch - ARM

a. Station ARM light(s) - ON

b. Heads up ARM light - ON

Change 6

2-91

T.O. 1F-4C-34-1-1

Bomb Run

Approach the target at the preplanned release alti¬
tude and airspeed. When the aircraft is directly over
the IP, or when the pipper is on target, depress and
hold the bomb release button. Maintain a constant
airspeed, altitude, and course until the bomb is
automatically released. The pullup light will illumi¬
nate to indicate bomb release and will go out when
the bomb button is released. Wind corrections for
the bomb must be applied prior to depressing the
bomb button.

1. Bomb release button - DEPRESS AND HOLD

2. (SUU-7) Station ARM lights - MONITOR

a. Blinking light - Tubes remaining

b. Station ARM light out - All tubes have re¬
ceived a firing pulse.

Note

The station ARM lights will not monitor the
empty status of the flare dispenser SUU-38,
SUU-42. The station ARM light normally
goes out when all SUU-13's on that station
have timed out.

I OFFSET BOMBING/TARGET FIND

Before IP

1 .

6 .

10 .

11 .

12 .

Delivery mode selector knob - OFFSET BOMB
or TGT FIND

Sight mode selector knob - A/G
The optical sight reticle is electrically caged
to the RBL and to 0° in azimuth. The roll
tabs display aircraft attitude until target in¬
sert, then steering commands to the target.
Navigation mode selector knob - NAV COMP
HSI mode switches - NAV COMP
If the HSI indications are to be used, the NAV
COMP position must be selected.

(WSO) INS mode selector knob - NAV
(WSO) BDHI mode switch - NAV COMP
(WSO) Weapon delivery panel - SET

a. Activate switch - NORMAL

b. Tgt find switch - NORMAL

c. Range switch - AS REQUIRED
(WSO) WRCS input counters - SET

a. Target distance N/S - 100-ft increments

b. Target distance E/W - 100-ft increments

c. IP altitude MSL - 100-ft increments

d. Release range - 10-ft or 100-ft increments
(Offset bomb)

e. Release advance - Milliseconds (Offset
bomb, if required)

Weapon selector knob - RKTS & DISP or A
With RKTS & DISP selected, AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

Station select - LOADED STATION(S)
a. Green light(s) - ON
Master arm switch - ARM

a. Station ARM light(s) - ON

b. Heads up ARM light - ON

Note

The ADI will not provide steering if the weap¬
on selector knob is on ARM.

Bomb Run-Offset Radar IP

1. (WSO) Radar power - OPR

2. (WSO) Radar mode - MAP-PPI

3. (WSO) Antenna stab switch - NOR

4. (WSO) Cursor intensity - ADJUST

5. (WSO) Antenna elevation - ADJUST

6. (WSO) Scan switch - WIDE

7. (WSO) Radar range - R2 or R3

8. (WSO) Operate the along track cursor to posi¬
tion the range cursor over the RIP.

9. (WSO) Operate the cross track cursor to posi¬
tion the offset cursor over the RIP.

10. (WSO) Freeze button - PUSH ON

Note

• The along track cursor must be moved first
to initiate cursor control. Position the inter¬
section of the cursors over the REP and then
push the freeze button ON; the cursors begin
tracking the RIP. The cursors can be moved
to touch-up the intersection location over the
RIP after the Freeze button is pushed on.

11. (WSO) Target insert button - PUSH ON

12. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

When the aircraft is on course to the target
and at a preplanned release altitude and
airspeed, depress and hold the bomb release
button until the dispenser selected is empty.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target
counters will approach zero and then start
increasing in value.

13. (SUU-7) Station ARM lights - MONITOR

a. Blinking light - Tubes remaining.

b. Station ARM light out - AH tubes have re¬
ceived a firing pulse.

2-92

Change 5

T.O. 1F-4C-34-1-1

Note

The station ARM lights will not monitor the
empty status of the flare dispenser SUU-38,
SUU-42. The station ARM light normally
goes out when all SUU-13's on that station
have timed out.

Bomb Run-Visual IP Fly-Over

1. (WSO) When over IP, freeze button and target
insert button - PUSH ON

When the aircraft is directly over the IP, the
freeze button and the target insert button are
pushed ON simultaneously. The steering in¬
struments supply steering commands to the
target, and the cursors position and start
tracking the target. If the target is visible on
the scope, the WSO may touch-up the cursors
when the target elevation is set in the ALT
RANGE control.

2. Bomb release button - DEPRESS AND HOLD
(Offset bomb)

When the aircraft is on course to the target
and at a preplanned release altitude and true
airspeed, depress and hold the bomb release
button until the dispenser selected is empty.

Note

The roll tabs rotate as the target is passed,
and the BDHI and HSI distance-to-target

counters will approach zero and then start
increasing in value.

3. (SUU-7) Station ARM lights - MONITOR

a. Blinking light - Tubes remaining

b. Station ARM light out - All tubes have re¬
ceived a firing pulse.

Note

The station ARM lights will not monitor the
empty status of the flare dispenser SUU-38,
SUU-42. The station ARM light normally
goes out when all SUU-13's on the station
have timed out.

POST STRIKE

Before Landing

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) - AFT

7. Sight mode selector knob - STBY or CAGE

Armament Area (De-Arming)

1. Armament switches - OFF/SAFE/NORMAL

2. Aircrew - HANDS IN VIEW

A/B 45Y-1, Y-2, Y-4 SPRAY TANK DISPENSERS |F-4E|
AFTER T.O. 1F-4E-556

PREFLIGHT

Refer to part 4.

INFLIGHT

DISPENSING

1. Delivery mode selector knob - DIRECT

2. Station select - LOADED STATIONS
a. Green light - ON

3. Weapon selector knob - A

4. Arm nose tail switch - NOSE & TAIL

5. Master arm switch - ARM

a. Station ARM light - ON

b. Heads up ARM light - ON

Note

Placing the master arm switch to ARM arms
the A/B 45Y-1 tank causing an explosive
squib to discharge, thereby pressurizing the
bladder of liquid.

WARNING

Once the A/B 45Y-1 is armed, it cannot be
dearmed and therefore must not be brought
back to base.

Note

• On the A/B 45Y-2 dry agent spray tank, en¬
ergizing the master arm switch causes the
agent container to be pressurized by ram air
for proper dissemination. The Y-2 tank can
be dearmed by positioning the master arm
switch to SAFE.

• On the A/B 45Y-4 dry agent spray tank, en¬
ergizing the master arm switch arms the
tank. The Y-4 tank can be dearmed by po¬
sitioning the master arm switch to SAFE.

6. Bomb button - DEPRESSED

7. Station ARM light - MONITOR

a. Blinking station ARM light - spray remain¬
ing

b. Station ARM light out - no spray remaining

Change 5

2-93

T.O. 1F-4C-34-1-1

DISPENSER RELEASE

1. Station select - LOADED STATION(S)
a. Green light - ON

2. Selective jettison knob - STORES

3. Selective jettison button - PUSH

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) - AFT

7. Sight mode selector knob - STBY or CAGE

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF/SAFE/NORMAL

2. Aircrew - HANDS IN VIEW

TMU-28/B SPRAY TANK |F-4E) AFTER T.O. 1F-4E-556

PREFLIGHT Not.

Refer to part 4.

INFLIGHT

1. Weapon selector knob - B or C (Not in RKTS &
DISP or A)

2. Arm nose tail switch - SAFE

3. Master arm switch - SAFE
a. Heads up ARM light - OFF

DISPENSING

1. Delivery mode selector knob - DIRECT

2. Station select - LOADED STATION(S)
a. Green light(s) - ON

3. Master arm switch - ARM

a. Station ARM light(s) - OFF

b. Heads up ARM light - ON

4. To extend boom, weapon selector knob - A

a. While boom is extending, station ARM
light(s) - ON STEADY

b. Boom fully extended, amber light(s) -
BLINKING

5. To begin dispensing, bomb button - DEPRESS
AND HOLD (8 sec)

6. To stop dispensing, bomb button - RELEASE

7. Weapon selector knob - B or C (Not in RKTS &
DISP or A)

8. To retract boom, arm nose tail switch - NOSE
& TAIL

a. Station ARM light continues to blink after
boom is retracted.

The Station ARM light will continue to blink
until power is removed from the aircraft, ex¬
cept when the station selector button is pushed
off. When the station selector button is pushed
on, the light will begin blinking again.

9. Station select - PUSH OFF

a. Green lights) - OFF

b. Station ARM light(s) - OFF

10. Delivery mode selector knob - OFF

11. Master arm switch - SAFE
a. Heads up ARM light - OFF

DISPENSER RELEASE

1. Station select - LOADED STATION(S)
a. Green light(s) - ON

2. Selective jettison knob - STORES

3. Selective jettison button - PUSH

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) - AFT

7. Sight mode selector knob - ST BY or CAGE

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF/SAFE/NORMAL

2. Aircrew - HANDS IN VIEW

2-94

Change 5

T.O. 1F-4C-34-1-1

PAU-7/A SPRAY TANK |F-4E] AFTER T.O. 1F-4E-556

PREFLIGHT

Refer to part 4.

INFLIGHT

1. Weapon selector knob - B or C (Not in RKTS
& DISP or A)

2. Arm nose tail switch - SAFE

3. Master arm switch - SAFE

DISPENSING

1. Delivery mode selector knob - DIRECT

2. Weapon selector knob - A

3. Station select - LOADED STATION(S)

a. Green light(s) - ON

4. Master arm switch - ARM
a. Heads up ARM light - ON

5. To extend boom, arm nose tail switch - NOSE
& TAIL

6. To dispense, bomb button - DEPRESS & HOLD

Tank will dispense with boom up or down.

7. To stop dispensing, bomb button - RELEASE

8. To retract boom, arm nose tail switch - TAIL
(90 sec)

9. Station select - PUSH OFF (after boom retract)
a. Green light(s) - OFF

10. Delivery mode selector knob - OFF

11. Master arm switch - SAFE
a. Heads up ARM light - OFF

DISPENSER RELEASE

1. Station select - LOADED STATION(S)
a. Green light(s) - ON

2. Selective jettison knob - STORES

3. Selective jettison button - PUSH

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) - AFT

7. Sight mode selector knob - STBY or CAGE

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF/SAFE/NORMAL

2. Aircrew - HANDS IN VIEW

SUU-16/A, -23/A GUN POD |F-4E[ AFTER T.O. 1F-4E-556

PREFLIGHT

Refer to part 4.

INFLIGHT

1. Sight mode selector knob - A/G (or A/A unless
CAGE is present)

2. Reticle depression knob - SET (A/G only)

3. Gun clear switch - NONCLEAR or AUTO
CLEAR

4. Delivery mode selector knob - OFF or DIRECT

Note

• If the optical sight is to be used for air-to-
ground guns, the OFF or DIRECT position
should be selected on the delivery mode se¬
lector panel.

• Reference to the RAT (ram air turbine) is
applicable to the SUU-16/A gun pod only.

5. Weapon selector knob - NOT TV or ARM (un¬
less CAGE is present)

6. Wing station select - LOADED STATION(S)
a. Green light(s) - ON (SUU-23 prestart)

7. Guns/Missiles select switch - GUNS
a. Heads up GUN light - ON

8. Master arm switch - ARM

a. Heads up GUN light - OFF

b. Heads up ARM light - ON

c. Station ARM light(s) - ON (SUU-16, RAT
OUT)

The SUU-16 RAT is deployed when master
arm is placed to ARM.

9. Trigger switch - ACTUATE

a. Zero rounds remaining, station ARM light -
OFF

FINAL BURST SAFE GUNS
(Rounds Remaining)

1. Gun clear switch - AUTO CLEAR

2. Trigger switch - ACTUATE

3. Station select - PUSH OFF

a. Green light(s) - OFF

b. Station ARM light(s) - OFF (SUU-16, RAT
IN)

The SUU-16 RAT will retract when the
station selector button is pushed OFF.

4. Master arm switch - SAFE
a. Heads up ARM light - OFF

Change 5

2-95

T.O. 1F-4C-34-1-1

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches(5) - AFT

7. Sight mode selector knob - STBY or CAGE

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF/SAFE/NORMAL

2. Aircrew - HANDS IN VIEW

M61A1 NOSE GUN [F-4EI AFTER T.O. 1F-4E-556

PREFLIGHT

Refer to part 4.

EXTERIOR INSPECTION

(Not Applicable)

INFLIGHT

1. Sight mode selector knob - A/G (or A/A unless
CAGE is present)

2. Reticle depression knob - SET (A/G only)

3. Rate switch - HIGH/LOW

4. Rounds counter - SET

5. Delivery mode selector knob - OFF or DIRECT

Note

If the optical sight is to be used for air-to-
ground guns, the OFF or DIRECT position
should be selected on the delivery mode se¬
lector panel.

6. Weapon selector knob - NOT TV or ARM (un¬
less CAGE is present)

7. GUN station select - PUSH ON

a. Green GUN station light - ON

8. Guns/Missiles select switch - GUNS
a. Heads up GUN light - ON

9. Master arm switch - ARM

a. Heads up GUN light - REMAINS ON

b. Heads up ARM light - ON

c. Gun station ARM light - ON

10. Trigger switch - ACTUATE

a. Zero rounds remaining, station ARM light -
OFF

SAFE GUNS

1. GUN station select - PUSH OFF

a. Green GUN station light - OFF

b. Gun station ARM light - OFF

2. Master arm switch - SAFE
a. Heads up ARM light - OFF

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) -
AFT

7. Sight mode selector knob - STBY or CAGE

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF/SAFE/NORMAL

2. Aircrew - HANDS IN VIEW

AGM-12B, C, E MISSILES (F-4EJ AFTER T.O. 1F-4E-556

H-

PREFLIGHT

- h

Master arm switch - ARM

Refer to part 4.

a. Heads up ARM light - ON

b. All station ARM lights - OFF

INFLIGHT

Bomb button - DEPRESS

Control handle - TRANSMIT COMMANDS

The transmitter timer is energized for 50 ±

TRANSMITTER CHECK

10 seconds.

Master arm switch - SAFE

Perform an airborne check as follows:

1. Delivery mode selector knob - DIRECT

BEFORE MISSILE LAUNCH

2. Station select - OFF

a. Green lights - OFF

(AC, WSO) Oxygen diluter selector - 100 PER

3. Warning lights test sw - TEST

CENT

a. Station green lights - ON

Weapon selector knob - AGM-12

b. Station ARM lights - ON

Station select - PUSH ON

4. Weapon selector knob - AGM-12

a. Green light - ON

2-96

Change 5

T.O. 1F-4C-34-1-1

MISSILE LAUNCH

1. Master arm switch - ARM

a. Heads up ARM light - ON

b. Station ARM light - ON

2. Bomb button - DEPRESS (2 sec approx)

Depress and hold the bomb button until the
missile fires or until the launch is aborted
due to missile malfunction,
a. Station ARM light - OFF

To immediately arm a second missile for re-attack:

3. Station select (just fired) - PUSH OFF
a. Green light - OFF

4. Station select (next missile) - PUSH ON

a. Green light - ON

b. Station ARM light - ON

MISSILE FIGHT (AGM-12E)

To prevent AGM-12E warhead from functioning

1. (WSO) Armament power circuit breaker -
PULL (No. 1 panel)

If it is necessary to safe the missile, pull
circuit breaker.

AFTER MISSILE ATTACK

1. Armament switches - OFF/SAFE/NORMAL

a. Master arm switch - SAFE

b. Station selector buttons - OFF

2. Emergency vent handle - CYCLE

Pull to de-pressurize, then push to pres¬
surize to cycle cockpit air in case of contam
ination by missile exhaust gases.

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) -
AFT

7. Sight mode selector knob - STBY or CAGE

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF/SAFE/NORMAL

2. Aircrew - HANDS IN VIEW

SUU-21/A BOMB DISPENSER (MODIFIED) AFTER T.O. 1F-4E-556

PREFLIGHT bomb release

These procedures consider the employment of SUU-
21/A dispensers modified for use with pedestal panel
controls and inboard (stations 2 and 8) carriage only:

Refer to part 4, Cockpit Weapons Check and Exter¬
ior Inspection (SUU-21/A Dispenser).

interior inspection

If the dispenser doors are open, close the doors as
follows:

1. External power - APPLY

2. Generator switches - EXT ON

3. Armament safety override - DEPRESS

4. Station select - LOADED STATION
a. Green light - ON

5. Master arm switch - ARM

a. Heads up ARM light - ON

b. Station ARM light - ON

6. Arm nose tail switch - NOSE

a. Station ARM light - FLASHING (doors
closing)

b. Station ARM light - OFF (doors closed)

7. Station select - OFF
a. Green light - OFF

8. Master arm switch - SAFE

a. Heads up ARM light - OFF

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Weapon selector knob - BOMBS

5. AWRU - SET

a. Intrvl controls - (Not applicable)

b. Qty knob - 1

6. Station select - LOADED STATION
a. Green light - ON

7. Master arm switch - ARM

a. Station ARM light - OFF

b. Heads up ARM light - ON

8. Arm nose tail switch - NOSE & TAIL

a. Station ARM light - FLASHING (doors open
ing)

b. Station ARM light - ON (doors open)

9. Bomb button - DEPRESS

after final bomb release

1. Arm nose tail switch - NOSE

a. Station ARM light - FLASHING (doors clos¬
ing)

b. Station ARM light - OUT (doors closed)

2. Master arm switch - SAFE
a. Heads up ARM light - OFF

3. Station select - OFF
a. Station green light - OFF

4. Delivery mode selector knob - OFF

5. Sight mode selector knob - STBY or CAGE

Change 5

2-97

T.O. 1F-4C-34-1-1

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) - AFT

7. Sight mode selector knob - STBY or CAGE

AFTER LANDING ARMAMENT AREA (DE-ARMING)

To Open SUU-21/A Dispenser Doors:

1. Armament safety override button - DEPRESS

2. Station select - LOADED
a. Station green light - ON

3. Master arm switch - ON

a. Heads up ARM light - ON

b. Station ARM light - ON

4. Arm nose tail switch - NOSE & TAIL

a. Station ARM light - FLASHING (doors open
ing

b. Station ARM light - ON (doors open)

5. Station select - OFF

a. Station green light - OFF

6. Master arm switch - OFF
a. Head up ARM light - OFF

7. Armament switches - OFF/SAFE/NORMAL

8. Aircrew - HANDS IN VIEW

MODIFIED A/A 37U-15 TOW TARGET SYSTEM |F-4EJ AFTER T.O. 1F-4E-556

PREFLIGHT

Refer to part 4.

INFLIGHT

PRE-TAKEOFF

To reduce rolling tendencies immediately after take¬
off, the following aileron trim positions are recom¬
mended. Trim settings are the same with or without
centerline tank.

a. Dart system on station 1, station 9 empty: 2.5
inches left aileron down (trim 2.5 seconds to right of
neutral), 1.5 inches right rudder (trim 1.5 seconds to
right of neutral).

b. Dart system on station 1, external fuel tank on
station 9: 3.5 inches right aileron down (trim 3.5
seconds to left of neutral), 1.0 inch left rudder (trim
1.0 seconds to left of neutral).

Note

The tow target system, carried on the left
outboard wing station, may induce 20° to 30°
errors in the remote compass transmitter.

Due to this effect, the DG mode on the com¬
pass controller should be selected.

TAKEOFF

Initiate a slow pitch rotation at 140 KIAS to obtain 8°
pitch attitude indicated on the ADI for liftoff at 180 to
190 KIAS. Decrease thrust after gear and flap re¬
traction to ensure that 275 KIAS is not exceeded.

Note

Refer to T.O. 1F-4C-1 External Store Limita¬
tions for A/A 37U-15 Tow Target System in¬
flight limitations.

TARGET DEPLOYMENT

1. Delivery mode selector knob - DIRECT

2. Weapon select - A

3. Station select - LO

a. LO green light - ON

4. Arm nose tail switch - SAFE

5. Master arm switch - ARM

a. Head-up ARM light - ON

b. Station ARM light - ON

6. Bomb button - DEPRESSED

Depressing the bomb button once deploys the
the target.

[caljtion|

Do not attempt to deploy a damaged dart tar¬
get. Motion of the damaged target after re¬
lease is unpredictable. Possible contact with
the aircraft could be hazardous.

7. Master arm switch - SAFE
a. ARM lights - OFF

CABLE CUT

1. Master arm switch - ARM

a. Head-up ARM light - ON

b. Station ARM light - ON

2. Tow cable - CUT

a. (before Rev K) Bomb button - DEPRESS

b. (after Rev K) Arm nose tail switch - NOSE

3. Chase plane, acknowledge cable cut

Emergency Cut

1. If cable does not cut, arm nose tail switch -
NOSE and TAIL or TAIL

2. Chase plane, acknowledge cable cut

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) - AFT

7. Sight mode selector knob - STBY or CAGE

Change 7

2-98

T.O. 1F-4C-34-1-1

LANDING WITH STOWED TARGET (DAMAGED OR ARMAMENT AREA (DE-ARMING)

UNDAMAGED)

1. Armament switches - OFF/SAFE/NORMAL

1. Flaps - 1/2 2. Aircrew - HANDS IN VIEW

2. Angle of attack - 17 to 18 UNITS

(With wing tank use less than 17 units).

INFLIGHT PROCEDURES FOR BOMBING RANGE SELECTED WEAPONS

|F-4E| AFTER T.O. 1F-4E-556

INFLIGHT

ROCKET LAUNCHERS AND SUU-20

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Weapon select - RKTS & DISP or A

5. With RKTS & DISP selected, AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

6. Station select - LOADED STATIONS)
a. Green light(s) - ON

7. Master arm switch - ARM

a. Station ARM light(s) - ON

b. Heads up ARM light - ON

8. Bomb button - DEPRESS

BOMBS, SUU-20

Note

There is no cockpit indication to determine
that all bombs or rockets have been released
or fired from SUU-20 bomb/rocket dispenser.
The intervalometers within the SUU-20 cannot
be rehomed in flight for an attempt to release
or fire a hung bomb or rocket. Do not use an
aircraft interval setting of less than 0.100
second when using the SUU-20.

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Weapon selector knob - BOMBS

5. AWRU - SET

a. Intrvl controls - SET

b. Qty knob - SET

6. Arm nose tail switch - AS REQUIRED

With weapon selector knob in BOMBS, the
arm nose tail switch must be out of SAFE to
obtain the station ARM light.

7. Station select - LOADED STATION(S).
a. Green light(s) - ON

8. Master arm switch - ARM

a. Station ARM light(s) - ON

b. Heads up ARM light - ON.

9. Bomb button - DEPRESS

BOMBS, SUU-21/A (DCU-94/A)

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - AS REQUIRED

4. Weapon selector knob - BOMBS

5. Option selector knob - SAFE

6. Loaded station selector switch - FORWARD
a. WARN light - ON

7. (WSO) Nuclear consent switch - REL/ARM
a. WARN light - OFF

8. Option selector knob - GRD

a. WARN light - FLASH

b. WARN light - ON

9. Master release lock switch - FORWARD
a. UNLOCKED light - ON

10. Bomb button - DEPRESS

Note

To reopen doors during automatic operation,
repeat steps 5 and 8.

After Final Release (DCU-94/A)

1. Option selector knob - SAFE
a. WARN light - FLASH/OFF

2. Master release lock switch - AFT
a. UNLOCKED light - OFF

3. Loaded station selector switch - AFT

4. (WSO) Nuclear consent switch - SAFE

BOMBS-SUU-21/A MODIFIED

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. Delivery mode selector knob - DIRECT

4. Weapon selector knob - BOMBS

5. AWRU - SET

a. Intrvl controls - (Not applicable)

b. Qty knob - 1

6. Station select - LOADED STATION(S).
a. Green light(s) - ON

7. Master arm switch - ARM

a. Station ARM light(s) - OFF

b. Heads up ARM light - ON

8. Arm nose tail switch - NOSE & TAIL

a. Station ARM light - FLASHING (doors open¬
ing)

b. Station ARM light - ON (doors open)

9. Bomb button - DEPRESS

To Close Doors

1. Arm nose tail switch - NOSE

a. Station ARM light - FLASHING, THEN OFF

Change 6

2-98A

T.O. 1F-4C-34-1-1

STRAFE-SUU-16/A, 23/A, AND M61A NOSE GUN

1. Sight mode selector knob - A/G

2. Reticle depression knob - SET

3. (Nose Gun) Rate switch - HIGH/LOW

4. (Nose Gun) Rounds counter - SET

5. (SUU-16/23) Gun clear switch - NONCLEAR or
AUTO-CLEAR

6. Delivery mode selector knob - OFF or DIRECT

7. Weapon selector knob - NOT IN TV or ARM
(unless CAGE is depressed)

8. Station select - LOADED STATION(S)

a. Green light(s) - ON

9. Guns/Missiles select switch - GUNS
a. Heads up GUN light - ON

10. Master arm switch - ARM

a. Heads up GUN light - GUN PODS, OFF
(NOSE GUN, ON)

b. Heads up ARM light - ON

c. Station ARM light(s) - ON

11. Trigger switch - ACTUATE

a. Zero rounds remaining, station ARM light -
OFF

RANGE DEPARTURE

1. Sight mode selector knob - STBY or CAGE

2. Delivery mode selector knob - OFF

3. Station select - OFF

4. Master arm switch - SAFE

BEFORE LANDING

1. Master arm switch - SAFE

2. Station select - OFF

3. Delivery mode selector knob - OFF

4. Radar missile power switch - OFF

5. Selective jettison knob - OFF

6. All DCU-94/A station select switches (5) - AFT

7. Sight mode selector knob - STBY or CAGE

ARMING AREA (DE-ARMING)

1. Armament switches - OFF/SAFE/NORMAL

2. Aircrew - HANDS IN VIEW

2-98B

Change 5

T.O. 1F-4C-34-1-1

PART 4 NORMAL AIRCREW PROCEDURES

F-4C aE

TABLE OF CONTENTS

(PILOT) SYSTEM CHECK

ECM Pod Operation (Refer to T.O. 1F-4C-34-1-1-1)

Radar Scope Camera. 2-99

COMBAT WEAPONS

Cockpit Weapons Check. 2-100

Before Exterior Inspection .... 2-100

After Exterior Inspection. 2-100

Exterior Inspection, Bombs. 2-100A

Suspension Equipment. 2-100A

BLU-l/B, B/B, C/B, -27/B, A/B

Fire Bombs. 2-100B

BLU-52/B, A/B Chemical Bombs . 2-100B

Ml 17 GP, MC-1 Gas, M129E1, E2
Leaflet, MK 82, MK 83, MK 84,

and Ml 18 GP. 2-100C

SUU-30 Dispensers and Bombs . . 2-100D

M117 (Retarded) and MK82 Snakeye

Bombs. 2-100E

KMU-351/B (MK 84) and KMU-
370A/B (Ml 18) KMU-388/B
(MK 82) Laser Guided Bombs . . . 2-100J

MK 20 Mod 2 & Mod 3 (Rockeye II) . . 2-100K

M36E2 Incendiary Cluster Bomb. . . 2-100K

Exterior Inspection, Rockets.2-100L

Suspension Equipment.2-100L

LAU-3/A, -32A/A, B/A, -59/A, -68A/A

Rocket Launchers . 2-100M

Exterior Inspection, Dispensers . . . 2-100Q

Suspension Equipment. 2-100Q

SUU-7 Dispensers. 2-100S

SUU-13 Dispensers. 2-100T

SUU-36, -38 Dispensers. 2-100U

SUU-42/A Flare Dispenser .... 2-100W

SUU-25A/A Flare Dispenser . . . 2-100W

SUU-25B/A.C/A Flare Dispenser

(Single Carriage). 2-100V

Exterior Inspection, Spray Tanks A/B
45Y-1, -2, -4, PAU-7/A, TMU-

28/B. 2-100Y

Exterior Inspection, SUU-16/A,-23/A

Gun Pod . 2-100Z

Exterior Inspection, AGM-12B/C/E
Missiles. 2-100AB

TRAINING EQUIPMENT

Exterior Inspection, SUU-20/A, A/A,

B/A Bomb/Rocket Dispenser .... 2-100AE

Exterior Inspection, SUU-21/A Bomb

Dispenser. 2-100 AG

Exterior Inspection, Modified A/A

37U-15 Tow Target System. 2-100AH

Exterior Inspection, TDU-ll/B Tar¬
get Rocket (5-inch HVAR). 2-100AJ

(UTS) AN/AWM-19. 2-100AP

RMU-8/A Tow Target System .... 2-100AR

RADAR SCOPE CAMERA (F-4C/D/E)

AFTER ENGINE START

CAUTION

These procedures assume no film is installed in the
camera. With external electrical power applied, or
with the engines running, proceed as follows:

1. Radar power - STBY

2. Camera power switch - ON

a. Green continuity light - ON

b. Amber film-remaining light - ON

Without a magazine installed, the film-
remaining light illuminates.

Note

If the lights do not function, check that the
console light knob is full clockwise; or check
that the camera electrical connector is in¬
stalled.

3. Film magazine - INSTALLED

Open the camera door and install the maga¬
zine in the prescribed manner; execute the
installation procedure gently,
a. Insert magazine into clamps so that maga¬
zine is aligned with sprocket gear on top-
left side of camera.

Ensure magazine is seated against magazine
stops or damage to sprocket may occur. On
some cameras, the sprocket gear is spring
loaded so that the door will not close with film
magazine improperly installed.

b. Close camera door.

c. Amber film remaining light - OFF

When the door is closed, the amber light
goes off.

4. Witness mark switch - OFF

5. Acquisition rate selector - SET AS REQUIRED

6. Radar intensity control - FULL CLOCKWISE

7. Outer filter lever - ADJUST

Adjust the outer filter lever to obtain the de¬
sired video level.

The camera is now ready to take pictures.
When the amber light illuminates, the exposed
magazine should be removed and another in¬
serted in the camera as stated in steps (1) thru
(3) above. Camera operation can be stopped at
any time by placing the camera power switch
OFF.

8. Film title - INSERT

9. After 15 seconds, camera power switch - OFF
10. Film title - REMOVE

Change 8

2-99

T.O. 1F-4C-34-1-1

COCKPIT WEAPONS CHECK

BEFORE EXTERIOR INSPECTION
Before Electrical Power

IN ACCORDANCE WITH AFR 60-9 , THE AIRCREW IS REQUIRED
TO USE THIS CHECKLIST WHEN OPERATING THIS AIRCRAFT
WITH NON-NUCLEAR WEAPONS. HOWEVER, THE EXTERIOR
INSPECTIONS IN THIS CHECKLIST CONTAIN MISSION ESSEN¬
TIAL ITEMS WHICH THE AIRCREW IS NOT REQUIRED TO PER¬
FORM SINCE THE CORRECT LOADING OF SUSPENSION
EQUIPMENT AND WEAPONS IS THE RESPONSIBILITY OF
CERTIFIED LOAD CREWS. THE EXTERIOR CHECKS PRE¬
CEDED BY A STAR (★) ARE CONSIDERED SAFETY OF FLIGHT
ITEMS WHICH SHOULD BE CHECKED BY AN AIRCREW
MEMBER IF TIME PERMITS. THE MISSION ESSENTIAL ITEMS
MAY BE PERFORMED IF DESIRED.

| caution" -

DO NOT PLACE THE GENERATOR CONTROL SWITCH ES
TO EXT ON UNTIL EXTERNAL POWER HAS BEEN CON¬
NECTED AND HAS REACHED RATED VOLTAGE AND
FREQU ENCY (400 CYCLES, 115/ZOO VOLTS AC).

F-4C/D/E BEFORE T.O. 1F-4E-556

1. AF FORM 781 -CHECK

2. WING STATION JETTI SON SWITCH - NORMAL

I^CAUTION^j

THE EXTERNAL WING TANKS CAN BE JETTISONED
BY THE EXTERNAL WING TANK JETTISON SWITCH
ANY TIME ELECTRICAL POWER IS ON THE AIRCRAFT.

3. INTERNAL WING DUM P SWITCH - N ORMAL

| CAUTION^|

WITH ELECTRICAL POWER APPLIED TO THE AIR¬
CRAFT WING FUEL WILL BE DUMPED ANY TIME THE
INTERNAL WING DUMP SWITCH IS IN THE DUMP POSITION.

4. GEAR HANDLE -DOWN

5. MISSILE JETTISON SELECTOR KNOB - OFF

6. MISSILE ARM SWITCH - SAFE

7. MASTER ARM SWITCH - SAFE

8. GENERATOR SWITCHES -OFF

AFTER EXTERIOR INSPECTION

Armament Area (Arming)

1. ARMAMENT SWITCH ES - OFF/SAFE

2. ARMAMENT SAFETY OVERRIDE BUTTON - PUSH IN

WARNING |

WHEN THE ARMAMENT SAFETY OVERRIDE BUTTON
IS ENERGIZED, THE JETTISON CIRCUIT IS PLACED
IN AN INFLIGHT CONFIGURATION, THE AC HAS A JETT¬
ISON CAPABILITY DURING TAKEOFF WHILE WEIGHT IS
ON THE GEAR.

3. AIRCREW -HANDS IN VIEW

THE AIRCREW WILL PLACE BOTH HANDS IN VIEW AS A
SIGNAL TO THE LOAD CREW TO APPROACH THE
AIRCRAFT, REMOVE ALL SAFETY PINS AND INSTALL
ALL ACCESS COVERS, AND PERFORM ANY FINAL AIR¬
CRAFT/WEAPON PREPARATIONS.

F-4E AFTER T.O. 1F-4E-556

1. AF FORM 781 -CHECK

2. INTERNAL WING DUMP SWITCH -NORMAL

PcAUTION^'l

WITH ELECTRICAL POWER APPLIED TO THE AIRCRAFT
WING FUEL WILL DUMP ANY TIME THE INTERNAL WING
DUMP SWITCH IS IN THE DUMP POSITION.

3. GEAR HANDLE -DOWN

4. MASTER ARM SWITCH -SAFE

5. DELIVERY MODE KNOB -OFF

6. JETTISON SELECTOR KNOB -OFF

7. GENERATOR SWITCHES -OFF

4C—34—l—l-(138)

Figure 2-20A

2-100

Change 5

T.O. 1F-4C-34-1-1

HOMING

U«HT

SAFETY

i, ****

HOMING

ROCKET

BOMBS

MER/TER ELECTRIC SAFETY PIN

SUSPENSION EQUIPMENT

1. ARMAMENT PYLON - CHECK

a. PYLONSAFETY PIN -INSTALLED
* b. EJECTOR CARTRIDGES -INSTALLED

c. INFLIGHT SAFETY LOCKOUT PIN -INSTALLED

d. LOCK INDICATOR - UNLOCKED

e. SWAYBRACES- TIGHTENED

2. CENTERLINE RACK - CHECK

a SAFETY PIN -INSTALLED (REMOVED PRIOR TO
ENGINE START)

★ b. EJECTOR CARTRIDGES - INSTALLED

c. SWAY BRACES ON CENTERLINE ADAPTER -

TIGHTENED

3. MER/TER - CHECK

a. ELECTRICAL SAFETY PIN- INSTALLED

b. EJECTOR RACK SAFETY PIN - INSTALLED

★ c. EJECTOR RACK CARTRIDGES -INSTALLED

CARTRIDGES ARE REMOVED IF BREACH CAP
CABLE CAN BE PUSHED INTO BREACH

d. SHORTING PLUG -INSTALLED

e. EJECTOR FOOT -SEATED AGAINST WEAPON

f. SWAYBRACES- TIGHTENED

★ SAFETY OF FLIGHT ITEM

SPECIAL WEAPON V
JWUGHY ■

SPECIAL WlAPON I

INW8W LOCK I « V

MANUAL **UA5t

GROUND SAFET Y
PIN HOOK LOCK

CAUTION

TO*** CARTRIOGC If KID SHAW IS
«f TAtNEt* TO ^ ^ VISItLE HOOK
iS UNLAYCHID

• 0 CAUTION hi auAira
uratt uucwwwi

Figure 2-21 (Sheet 1 of 10)

Change 4

2-100A

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

BOMBS

(CONTINUED) f

BLU-1/B, B/B, C/B, -27/B, A/B
Fire Bombs

CENTERLINE

BLU-52/B, A/B Chemical Bombs

NORMAL

FORWARD SUSPENSION

OUTBOARD

NORMAL

FORWARD SUSPENSION

★ 1. (UNFINNED) MER POSITION- FORWARD

★ 2. (FINNED) MER POSITION - AFT

3. INITIATOR SAFETY/SHEAR WIRE - INSTALLED

4. ARMING LANYARD - CONNECTED

5. NOSE AND TAIL CAPS -SECURE

★ 6. FIN CONFIGURATION - (X)

7. FIRE BOMB - SECURE NO LEAKS

★ SAFETY OF FLIGHT ITEM

FMU-7C/B FIRE BOMB INITIATOR

Figure 2-21 (Sheet 2 of 10)

2-100B

Change 5

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

BOMBS

STATIONARY EYELET

ARMING PIN

M117 GP, MC-1 Gas,

M129E1, E2 LEAFLET,

MK82, 83, 84 & M118GP Bombs

★ 1. MER POSITION - CHECK

a. M117, MC-1, M129E1, MK 82 - FORWARD

b. MK 83 OUTBOARD - AFT

c. MK 83 CENTERLINE - FORWARD

★ 2. FIN CONFIGURATION -CHECK

a. M117, MC-1, M129E1, E2 ON AIRCRAFT STATIONS 1 AND
9, OUTBOARD MER REAR SHOULDER POSITIONS -
PLUS, ALL OTHER STATIONS - (X)

b. MK 83 - PLUS

c. MK82, MK 84, M 118 -(X)

3. ARMING WIRES AND STEEL CLIPS - INSTALLED

★ 4. FUZES -CHECK RECORDED FUZE SETTINGS

★ SAFETY OF FLIGHT ITEM

TYPICAL NOSE AND
TAIL ARMING WIRE
ROUTING

SWIVEL & LOOP
ASSEMBLY

ARMING

WIRE

AN-M147A1 ARMINGWIRE

VANE EYELET

ARMING

WIRE

ARM NG VANE

Figure 2-21 (Sheet 3 of 10)

Change 7

2-100C

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION V

(CONTINUED)

SUU-30 DISPENSERS AND BOMBS

BOMBS

26/B
36/B
59/B
61A/B
85/B

61A/B
63/B
86/B

ARMING

WIRE

■■■Hi HI

SWIVEL & LOOPS
— (ARMING WIRE PASSES
THRU LARGE LOOP)

AND LINKS \

HiTTiTl

i ■!

TTTTYiiTTO:

L3E333

nJuVjUUl

H 1 ^ 1H1 i U i IH ^

'ITWiWfl

T.O. 1F-4C-34-1-1

exterior inspection

4. FMU-56A/B, B/B FUZE -CHECK RECORDED
SETTINGS

a. PITOT TUBE - RETRACTED

[ WARNING I

IF THE PITOT TUBE IS EXTENDED, THE FUZE
MUST BE TREATED AS ARMED AND APPROPRI¬
ATE AUTHORITIES SHOULD BE NOTIFIED IMMEDI¬
ATELY.

b. HEIGHT OF BURST (HOB) SWITCH - SET AS

BRIEFED

BOMBS

c. ARMING TIMER SWITCH - SET AS BRIEFED

d. ECM SWITCH - SET AS BRIEFED

e. LANYARD, SWIVEL & LINKS - SECURE
5. M907 FUZE

a. ARMING WIRE, SWIVEL & LOOPS - SECURE

b. FOIL DISC - NOT PUNCTURED

c. ARMING TIME -SET AS BRIEFED

d. STEEL CLIP - INSTALLED

M117R & MK82 SNAKEYE

★ 1. MER POSITION - FORWARD

★ 2. LOAD CONFIGURATION - SINGLE OR RIPPLE

RELEASE

★ 3. FIN CONFIGURATION -(X)

4. (M117R) MAU-91A/B OR MAU-91B/B FIN USED

★ 5. (H/L) ARMING WIRE CONFIGURATION - CHECK

★ a. NOSE FUZE ARMING WIRE TIED TO AFT LUG WITH

SWIVEL AND LOOP IN NOSE ARMING SOLENOID

★ b. TAIL FUZE ARMING LANYARD AND FIN RELEASE

LANYARD/WIRE ATTACHED TO A SWIVEL AND LINK:
SWIVEL AND LINK IS IN TAIL ARMING SOLENOID.

★ 6. FUZES -CHECK RECORDED FUZE SETTING

★ a. (H/L) M904E2/E3 NOSE FUZE - 6.0 SEC MINIMUM

★ b. (H/L) FMU-54 TAIL FUZE - 2.5 SEC MINIMUM

★ c. (M904E2/E3) STEEL CLIP - INSTALLED

★ 7. (M117R) FAHNESTOCK CLIP INSTALLED ON REAR OF FIN

LATCH ASSEMBLY RELEASE PIN.

8. (M117R) FIN RELEASE LANYARD LOOP AT AFT END OF
CHANNEL SECURED BY STAINLESS STEEL SAFETY WIRE.

Nof |

WHEN FMU-54 IS NOT INSTALLED AND WHEN HIGH DRAG ONLY
CONFIGURATION IS DESIRED, THE NOSE ARMING WIRE IS SECURED
TO THE AFT END OF THE TAIL FIN; SWIVEL AND LOOP TO NOSE
SOLENOID IS NOT USED.

9. (MK 82) FAHNESTOCK CLIP INSTALLED
(AGAINST GUIDE TUBE) ON FIN REL WIRE
WITH 4 INCHES OF WIRE EXTENDING
AFT OF FIN. (See sheet 6)

★ SAFETY OF FLIGHT ITEM

(H/L) = HIGH/LOW DRAG INFLIGHT OPTION 40.34.,.,.,139.5,

Figure 2-21 (Sheet 5 of 10)

Change 7

2-100E

exterior inspection >*

BOMBS

(CONTINUED)

SAFETY

CLIP

LOCKING

PLATE

DELAY¬

SETTING

THUMBWHEEL

(IMPACT)

LOCKING

PLATE

FUZE

Figure 2-21 (Sheet 6 of 10)

2-100F Change 7

4C - 34 - 1 -1 -(139 -* )

FMU-81/B SHORT DELAY FUZE

T.O. 1F-4C-34-1-1

BOMBS

H = NOSE SOLENOID
T _ TAIL SOLENOID
+ POSITIVE ARMING, FINS MUST
OPEN TO ARM FUZE.

Mill GP BOMB (RETARDED)

NOSE ARMING WIRE—v

FIN RELEASE LANYARD

M904-E2, E3

NOSE ARMING
WIRE TIED
^ TO LUG —

'zPt 1

TAIL FUZE LANYARD —> 1 — FMU-54

(HIGH OR LOW DRAG COCKPIT SELECTABLE)

TAIL FUZE LANYARD-

NOSE ARMING WIRE-
M904-E2, E3V5

FMU-54/B
FUZE —

FIN RELEASE LANYARD NOSE

r- ARMING WIRE

FIN RELEASE
LANYARD
-SAFETY WIRED

(HIGH DRAG FUZE SELECTABLE)

,— FIN RELEASE LANYARD

NOSE ARMING WIRE -

M904-E2/E3,

NOSE ARMING WIRE-

M904-E2/E3„

(HIGH OR LOW DRAG COCKPIT SELECTABLE)

0 T /—FIN RELEASE LANYARD

NOSE

ARMING WIRE
SECURED WITH
FERRULE

FIN RELEASE
LANYARD
-SAFETY WIRED

— NOSE

ARMING WIRE
SECURED WITH
FERRULE

FINE RELEASE
LANYARD
SAFETY
-WIRED

(HIGH DRAG ONLY) _

/-FIN RELEASE LANYARD

MI110 (HIGH DRAG ONLY)

UPPER ARMING WIRE -

MK30, MK32
ARMING DEVICE-*^

LOWER ARMING WIRE

FIN RELFASE LANYARD

,-POPOUT PIN ARMING WIRE

FIRING r~
MECHANISM •"

ARM

SWITCH

DRAG

FUZE ARM

NOSE

LOW

HOSE ONLY

TAIL

HIGH

TAIL ONLY

N & T

HIGH

NOSE & TAIL

ARM

SWITCH

DRAG

FUZE ARM

NOSE

HIGH

+ NOSE ONLY

TAIL

LOW

DUD

N&T

HIGH

+ NOSE & TAIL

ARM

SWITCH

DRAG

FUZE ARM

NOSE

LOW

NOSE

TAIL

HIGH

+ NOSE

N&T

HIGH

NOSE

- 1

ARM

SWITCH

DRAG

FUZE ARM

NOSE

LOW

DUD

TAIL

HIGH

+ NOSE

N&T

HIGH

+ NOSE

ARM

SWITCH

DRAG

FUZE ARM

NOSE

LOW

DUD

TAIL

HIGH

TAIL

N&T

HIGH

TAIL

ARM

SWITCH

DRAG

FUZE ARM

NOSE

LOW

DUD

TAIL

HIGH

DUD

Figure 2-21 (Sheet 7 of 10)

Change 6

2-100G

T.O. 1F-4C-34-1-1

(CONTINUED)

SSjSlWRPS I smaig

N - NOSE SOLENOID
T = TAIL SOLENOID
+ POSITIVE ARMING, FINS MUST
OPEN TO ARM FUZE.

Figure 2-21 (Sheet 8 of 10)

2-100H

Change 6

T.O. 1F-4C-34-1-1

! EXTERIOR INSPECTION

(CONTINUED)

BOMBS

KMU-351/B (MK-84) and
KMU-370A/B (M118)

KMU-388/B (MK 82)

Laser Guided Bombs

1. IR DOME WINDOW - NO DAMAGE

CHECK IR DOME WINDOW FREE OF CRACKS/SCRATCHES
OR DAMAGE.

2. DETECTOR HEAD - FREE TO SWIVEL

3. CANARDS - SECURE

4. THERMAL BATTERY ARMING WIRE AND STEEL CLIP -

INSTALLED

5. THERMAL BATTERY SAFETY PIN - REMOVED

6 . FMU-26 FUZE LANYARD - INSTALLED

7. ATU-35 SERIES ARM. WIRE & STEEL CLIP - INSTALLED

8 . BOMB AFT WING ASSEMBLY -SECURE

4C-34-1-1—(139-9)

Figure 2-21 (Sheet 9 of 10)

Change 8

2-100J

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

BOMBS

(CONTINUED)

MK 20 MOD 2 & MOD 3

1. MER POSITION -FORWARD

2. FUZE COVER - REMOVED

3. FUZE SAFE/ARM INDICATOR - SAFE

THE FUZE IS SAFE WHEN END OF INDICATOR PIN IS NOT
VISIBLE. THE FUZE IS ARMED WHEN END OF INDICATOR
PIN (FLAT SIDE PAINTED RED) IS VISIBLE AT BASE OF
PLASTIC INDICATOR BUBBLE. IF FUZE IS ARMED, NOTIFY
APPROPRIATE PERSONNEL IMMEDIATELY.

4 (MOD 3) FUZE OPTION WIRE - INSTALLED (T SOLENOID)

5. OPTION TIMER DIAL -SET AS REQUIRED

6. FUZE ARMING WIRE - INSTALLED (N SOLENOID)

7. FUZE WARNING TAG AND SAFETY DEVICES - REMOVED

8. FIN RELEASE BAND WIRE - INSTALLED (GUN
REMOVAL PIN)

9. FIN RELEASE BAND SAFETY PIN -REMOVED

M36E2 INCENDIARY CLUSTER BOMB

★ 1. M36E2 IDENTIFICATION - CHECK

CHECK STENCIL ON SIDE OF EACH WEAPON; THE M36
(NOT M35) MUST BE ABOARD (M36 AND M35 APPEAR
IDENTICAL).

★ 2. MER POSITION - FORWARD
3. NOSE FAIRING -REMOVED

4 ARMING WIRES - INSTALLED (N & T SOLENOIDS)

★ 5. FINS -

a. FIN CONFIGURATION -(X)

b. FINS DO NOT TOUCH OR OVERLAP FINS OF ADJACENT
WEAPON.

6 . TAIL FUZES (2)- CHECK

a FUZE TIME SETTINGS - MISSION REQUIREMENT

b. STEEL CLIP - INSTALLED

★ SAFETY OF FLIGHT ITEM

M36E2 INCENDIARY
CLUSTER BOMB (M152A1 FUZE)

4C-34-1-1-0 39-10)

Figure 2-21 (Sheet 10 of 10)

2-100K

Change 6

CMLE 53 - 103 ;

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

ROCKETS

1 MER/TER ELECTRIC SAFETY PIN

SUSPENSION EQUIPMENT

1. ARMAMENT PYLON -CHECK

a. PYLON SAFETY PIN - INSTALLED

★ b. EJECTOR CARTRIDGES - INSTALLED

c. INFLIGHT SAFETY LOCKOUT PIN - INSTALLED

d. LOCK INDICATOR - UNLOCKED

e. SWAYBRACES- TIGHTENED

2. CENTERLINE RACK - CHECK
a. SAFETY PIN - INSTALLED

(REMOVED PRIOR TO ENGINE START)

★ b. EJECTOR CARTRIDGES -INSTALLED

MER-10A/TER-9A ELECTRIC SAFETY PIN

c. SWAY BRACES ON CENTERLINE ADAPTER -TIGHTENED
3. MER/TER -CHECK

a. ELECTRICAL SAFETY PIN - INSTALLED

b. EJECTOR RACK SAFETY PIN - INSTALLED
★ c. EJECTOR RACK CARTRIDGES -INSTALLED

CARTRIDGES ARE REMOVED IF BREACH CAP CABLE
CAN BE PUSHED INTO BREACH.

d. UNUSED EJECTOR STATIONS, SHORTING PLUG -
INSTALLED

e. EJECTOR FOOT - SEATED AGAINST WEAPON

f. SWAYBRACES- TIGHTENED

★ SAFETY OF FLIGHT ITEM

HSISiS

SPECIAL WEAPON V

m*mm fr f K a $4

LOCKOUT pin^TOF
SPECIAL WlAPON . „ (

tNfUGm LOCK ifi

MANUAL HUAM 'jj&oCK

■ .!. . ~

4 C- 34 — 1 — l-( 140 - 1 )

Figure 2-22 (Sheet 1 of 2)

Change 4

2-100L

CMLE-503

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

ROCKETS

CENTERLINE

MER SHIFTED AFT

(CONTINUED)

★ 1. MER POSITION -AFT

★ 2. (OUTBOARD TER SHOULDER) WITH AIRCRAFT STATION 1/9
LOADED, EJECTOR RACK CARTRIDGE - REMOVED

3. MER/TER SWITCH - ROCKETS

4. (MER/TER CARRIAGE) ROCKET HARNESS (BLUE) -

CONNECTED

5 . (LAU-3/A SINGLE CARRIAGE ON MAU-12) SHORTING PIN
AND ELECTRICAL CABLE - INSTALLED

6. LAU-3/A. LAU-59/A, -68A/A,) SHORTING PIN -

LAU-68 A SHORTING PIN

WARNING

INSTALLED

7. (LAU-32B/A, -59/A, -68A/A) LAU DIAL INDICATOR - ARM

8. (LAU-32B/A, -59/A, -68A/A) LAU SELECTOR SW -

SINGLE/RIPPLE

9. (LAU-3/A, -32A/A) INTERVALOMETER - INSTALLED

★ 10. LAUNCHERS -SECURE, PROPER STA., CONDITION

★ 11. NOSE AND TAIL FAIRINGS - LOCKED

TWIST OR PUSH DOWN ON FAIRING. LOCK INDICATING
ARROWS NEED NOT BE ALIGNED IF THE FAIRING IS
LOCKED.

12. ROCKET MOTOR IGNITER CONTACT- TOUCHING
LAUNCHER GROUND FIRING CONTACT

13. ROCKET QUANTITY AND WARHEAD - MISSION

REQUIREMENT

★ SAFETY OF FLIGHT ITEM

4C-34—1—1—(140 -2)

Figure 2-22 (Sheet 2 of 2)

"All data on pages 2-lOON and 2-100P deleted."

2-100M

Change 7

T.O. 1F-4C-34-1-1

STe . Howms '

ij^USHT SAFETY

.«OMIKO S>

SQCKeT

*P*«Al WEAPdj*
LOCK UNtO/% ,

1 HOOK 7 \

f *tLtAit _— , ,

CAUTION

rOftQUC »» *f» ** A*T*S

«f AINLKS TO A ^ V»$»»U HOOK
1aftfr<9»9 IN P L* UNLATCHED

• 4i CAUTION mt «hja*d

MtKWHF ATTACHING M*S

★ SAFETY OF FLIGHT ITEM

SUSPENSION EQUIPMENT

1. ARMAMENT PYLON - CHECK

a. PYLON SAFETY PIN - INSTALLED

★ b. EJECTOR CARTRIDGES - INSTALLED

c. INFLIGHT SAFETY LOCKOUT PIN - INSTALLED

d. LOCK INDICATOR -UNLOCKED

e. SWAYBRACES- TIGHTENED

2. CENTERLINE RACK - CHECK
a. SAFETY PIN - INSTALLED

(REMOVE PRIOR TO ENGINE START)

★ b. EJECTOR CARTRIDGES - INSTALLED

C. SWAY BRACES ON CENTERLINE ADAPTER -TIGHTENED

3. MER/TER -CHECK

a. ELECTRICAL SAFETY PIN - INSTALLED

b. EJECTOR RACK SAFETY PIN - INSTALLED

★ c. EJECTOR RACK CARTRIDGES - INSTALLED

CARTRIDGES ARE REMOVED IF BREACH CAP CABLE
CAN BE PUSHED INTO BREACH.

d. UNUSED EJECTOR STATIONS, SHORTING PLUG -
INSTALLED

e. EJECTOR FOOT - SEATED AGAINST WEAPON

f. SWAYBRACES- TIGHTENED

FWD

me m wiAPow;v._
infix**?

lockout pm
SPECIAL WEAPON t \

mm<wi lock Imt

EXTERIOR INSPECTION

MER/TER ELECTRIC SAFETY PIN

DISPENSERS

4C-34-1-1—(141_t

Figure 2-23 (Sheet 1 of 7)

Change 4

2-100Q

EXTERIOR INSPECTION

STOW PLUG

DISPENSER NOSE PLUG

Sra^SSHi55il .

i 1 1 hk^ 1

\ T a

% _

T.O. 1F-4C-34-1-1

ELECTRICAL RECEPTACLE PLATE

MER POSITION - FORWARD

MER AND TER SWITCH - CBU

CBU HARNESS (YELLOW) - DISCONNECTED

DISPENSER NOSE PLUG - INSTALLED

ELECTRICAL RECEPTACLE -FIOO OR F105 POSITION

TUBE RELEASE SETTING - RECORDED

BALLAST BAND - INSTALLED ( EXCEPT SUU-7C/A)

EXPLOSIVE DETENTS - SECURE

(CBU—1, -2) TUBE EXTENSIONS - INSTALLED

TUBE EXTENSIONS

10. (SUU-7C/A) PUSH BUTTON SAFETY PIN - INSTALLED

★ SAFETY OF FLIGHT ITEM

US?

4C-34-1-1-( 141_3)

Figure 2-23 (Sheet 3 of 7)

Change 5

2-100S

SUU-7 DISPENSERS and BOMBS

4A/B

3/B

BDU-28/B

17/B

66/B

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

8 > _ _ ,

DISPENSERS

(CONTINUED)

SUU-13 ELECTRIC RECEPTACLE PLATE

SUU-

CBU-

■ 1 !■■■ fiW

13A/A

38/A

38A/A

1 » t

F-WO F-105

ALIGN ARROWS FOR US£ ON INDICATOR

SUU-13 DISPENSERS

SUU- 13 DISPENSERS & BOMBS

BLU-

39/B23
18/B
49/B
49A/B

★ 1. MER POSITION -FORWARD

★2. LOAD CONFIGURATION- RECORD FOR IN FLT REF.

3. MER AND TER SWITCK- CBU

4. CBU HARNESS (YELLOW) - DISCONNECTED

5. DISPENSER SAFETY PALLET - REMOVED

6. DISPENSER INTERVALOMETER SAFETY PIN -INSTALLED

7. DISPENSER INTERVALOMETER - SET AS REQUIRED

8. REAR FAIRING ON FORWARD MER STATIONS -REMOVED,
OR BOBTAIL DESIGN

9. ELECTRICAL RECEPTACLE- F105 POSITION
★ SAFETY OF FLIGHT ITEM

nW VI8/ ¥20/

lyYvY^

, /28A /34A /39

^FORWARD

BOTTOM VIEW

Figure 2-23 (Sheet 4 of 7)

4C-34—1-1-(141—4)

2-100T

Change 5

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

DISPENSERS

(CONTINUED)

1 «"■ 5 '

SUU-38 DISPENSERS & BOMBS

IQD^i

42/A

54/B

★ 1. MER POSITION - (STA 1/9) AFT. (STA 5) FWD

2. MER AND TER SWITCH - CBU

3. CBU HARNESS (YELLOW) - CONNECTED

4. INTERVALOMETER - SET AS REQUIRED

5. DISPENSER INTERVALOMETER SAFETY PIN - INSTALLED

6. ELECTRICAL RECEPTACLE - F105 POSITION

7. DISPENSER SAFETY PALLET - REMOVED

★ SAFETY OF FLIGHT ITEM

SUU-25A/A

END PLUGS ■:

SUU-25A/A FLARE DISPENSER

1. MER POSITION - FORWARD

2. MER SWITCH - ROCKET

3. ROCKET HARNESS (BLUE) -CONNECTED

4. DISPENSER TUBE SAFETY PINS (2) - INSTALLED

5. EXPLOSIVE DETENTS (8) - INSTALLED SEATED

G. FLARES/MARKERS -QUANTITY, TYPE, EJECTION
& IGNITION TIME

4C-34-1-l-(141_5

Figure 2-23 (Sheet 5 of 7)

Change 9

2-100U

nt»-ao

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

DISPENSERS

(CONTINUED)

SUU-25B/A, C/A FLARE DISPENSER

MER Carriage

★ l. MER SHIFTED - FORWARD

2. MER SWITCH - ROCKET

3. ROCKET HARNESS (BLUE) -CONNECTED

4. (SUU-25C/A) SHORTING PIN - INSTALLED

5. NOSE CONE - SECURE

6. FLARE RETAINING ASSEMBLY- CHECK
a. SHEAR PINS - INSTALLED

7. FLARES/MARKERS -QUANTITY, TYPE, EJECT &
IGNITION TIME

Single Carriage on MAU-12 Pylon

1. (SUU-25C/A) SHORTING PIN - INSTALLED

2. NOSE CONE - SECURE

3. DISPENSER ELECTRICAL CABLE - CONNECTED

4. FLARE RETAINING ASSEMBLY - CHECK
a. SHEAR PINS - INSTALLED

5. FLARES/MARKERS- QUANTITY, TYPE, EJECT &
IGNITION TIME

★ SAFETY OF FLIGHT ITEM

4C-34-l-l-<141-6)

f W

SHEAR

SEALING

CAP

Figure 2-23 (Sheet 6 of 7)

2-100V

Change 9

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

DISPENSERS

(CONTINUED)

SUU-42/A DISPENSER

SUU-42/A FLARE DISPENSER

1. DISPENSER SAFETY PIN - INSTALLED

2. DISPENSER SELECTOR SWITCH -SINGLE OR RIPPLE

3. DISPENSER INTERVALOMETER - RECORDED

4. DISPENSER CABLE - CONNECTED, SECURE

5. MAU-12 EJECTOR FEET -SEATED AGAINST WEAPON

6. FLARES -QUANTITY, TYPE, EJECTION &
IGNITION TIME

★ 7. MAU-12 EJECTOR CARTRIDGES - INSTALLED

★ 8. DISPENSER FINS - SECURE, NOT BENT

★ SAFETY OF FLIGHT ITEM

—34 — 1 — 1—(141 —7)

Figure 2-23 (Sheet 7 of 7)
"All data on page 2-100X deleted."

* ITS. GOVERNMENT PRINTING OFFICE.- 1973— 769-640/196

Change 9

2-100W/(2-100X blank)

T.O. 1F-4C-34-1-1

hook *>* nUA '

EXTERIOR INSPECTION

SUSPENSION EQUIPMENT

1. ARMAMENT PYLON -CHECK

a. PYLON SAFETY PIN- INSTALLED
★ b. EJECTOR CARTRIDGES - INSTALLED

c. INFLIGHT SAFETY LOCKOUT PIN - INSTALLED

d. LOCK INDICATOR - UNLOCKED

e. SWAY BRACES -TIGHTENED

SPRAY TANK (A/B45Y-1, -2, -4)

1. (Y-l.Y-4) SAFETY PIN -INSTALLED

SAFETY PIN MUST BE REMOVED BEFORE FLIGHT
★ 2. TANKS - SECURE, PROPER STATION,
CONDITION

SPRAY TANK A/B

INFLIGHT LOCKOUT BOLT)

HL0.MAI

o<«

. % -SAFETY PIN

fOl/HO®

■■I

SPRAY TANK SAFETY PIN, A/B 45Y-1

45Y-1, -2, 4, PAU-7/A & TMU-28/B

WARNING

THE TMU-28/B LIQUID AGENT SPRAY TANK CONTAINS
A VX AGENT WHICH IS HIGHLY TOXIC AND CAN CAUSE
DEATH TO PERSONNEL. VX IS ONE OF THE “V”
SERIES NERVE GASES AND IS CLASSED AS A PERSIS¬
TENT LETHAL AGENT. THE AIRCREW MUST NOT MAKE
PHYSICAL CONTACT WITH THE SPRAY TANK UNLESS
WEARING IMPERMEABLE RUBBER GLOVES.

SPRAY TANK (PAU-7/A & TMU-28/B)

1. SPRAY TANK SAFETY PIN -INSTALLED

2. SPRAY TANK - SECURE, PROPER STATION,
CONDITION

★ 3. BOTTOM TWO FINS- REMOVED

★ 4. BOOM- RETRACTED

4C-34-1 —1—(142)

Figure 2-24

Change 4

2-lOOY

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

SUU-16/A, -23/A GUN POD

onoono

INFLIGHT :

LOCKOUT

BOLT |

icotour m

jSSSW-

j W sAFETY‘piMj>. C\

T° 40 °-SCO

OCA

A*M/WG

COIETJOIO

1. ARMAMENT PYLON- CHECK

a. PYLON SAFETY PIN - INSTALLED

b. EJECTOR CARTRIDGES - INSTALLED

c. INFLIGHT SAFETY LOCKOUT PIN - INSTALLED

d. LOCK INDICATOR - UNLOCKED

e. SWAY BRACES -TIGHTENED

2. CENTERLINE RACK -CHECK

a. SAFETY PIN -INSTALLED (REMOVED PRIOR
TO ENGINE START)

b. EJECTOR CARTRIDGES - INSTALLED

c. SWAY BRACES ON CENTERLINE ADAPTER -
TIGHTENED

SUU-16/A, -23/A GUN POD

1. AMMUNITION -LOADED

2. GUN FIRING LEAD -DISCONNECTED

3. RAT LEAD -DISCONNECTED (SUU-16/A)

4. (TRAINING) ROUNDS COUNTER -CHECK RECORD

5. RAT BLADES -CHECK (SUU-16/A)

6. STARTER MOTOR LEAD -DISCONNECTED(SUU-23/A)

7. RAT DOOR -CLOSED (SUU-16/A)

4C-34-1-1-044-1)

Figure 2-25 (Sheet 1 of 2)

2-100Z

Change 4

! FIRING LEAD
DISCONNECTED

STARTER MOTOR
LEAD DISCONNECTED

4C-34-1-1—(14 4-2)

Change 4 2-100AA

Figure 2-25 (Sheet 2 of 2)

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION H

SUU-16/A

SUU—16/A,—23/A GUN POD

FIRING LEAD RECEPTACLE

SUU-16/A

(CONTINUED)

’ .. - < # M i :i2 ' > v 8

RAT LEAD
RECEPTACLE

T.O. 1F-4C-34-1-1

ARMAMENT PYLON

tCCKOUT H

A*Ml# G

SOtfNOtP

EXTERIOR INSPECTION •

COCKPIT CHECK (BEFORE ELEC PWR)

1. AF FORM 781 - CHECK

Note 1

CHECK CRYSTALS (RECEIVFR AND TRANSMITTER)
INSTALLED AND MATCH MISSION REQUIREMENTS.

2. AF FORM 259 -CHECK

3. PERFORM CHECKS IN FIGURE 2-20A.

EXTERIOR INSPECTION

1. ARMAMENT PYLON - CHECK

a. PYLON SAFETY PIN - INSTALLED

b. (AGM-12B) EJECTION CARTRIDGES - REMOVED

c. (AGM-12C/E) EJECTOR CARTRIDGES - INSTALLED

d. INFLIGHT SAFETY LOCKOUT PIN - INSTALLED

e. LOCK INDICATORS- UNLOCKED

f. SWAY BRACES - TIGHTENED

2. (AGM-12B) LAU-34 LAUNCHER -CHECK

a. FORWARD MISSILE STOP- FLUSH WITH DETENT

b. SHEAR PIN - INSTALLED

c. JETTISON GUN PISTON SAFETY WIRE - INSTALLED

THE JETTISON GUN PISTON MUST BE SAFETYWIRED
AND LOCKED IN THE FULL AFT POSITION.

d. AFT LAUNCHER LINK-LOCK- DOWN

( AGM-12B MUST UK

f>N I OK TU

I N'T

row

Loire K

4C-34-1-1—(143-1)

Figure 2-26 (Sheet 1 of 3)

2-100AB

Change 4

T.O. IF-4C-34-1-1

exterior INSPECTION

AGM-12B/C/E MISSILE

(CONTINUED)

INITIATOR SQUIB SHORTING PIN (AGM-12B/C)

INITIATOR SQUIB
SHORTING PIN

ORDNANCE SW SAFETY PLUG AGM-12B

ORDNANCE

SWITCH

SAFETY PLUG

AFT BODY
SECTION

S wSSk I'lWAlBtft.' .

CENTER SECTION SAFETY DEVICES (AGM-12C/E)

LEVER AND ■
LANYARD ASSY B

SHEAR PINS (3)

BATTERY

SWITCH

PLUG

1 LANYARD TO

| HOOK L~ 'J

3. MISSILE -CHECK

a. CANARDS -SECURE

b. INITIATOR SQUIB SHORTING PIN - INSTALLED

c. (AGM-12E) HOB DIAL -SET

1 FORWARD AND AFT LOCK RING ASSEMBLIES - SECURE

e. UMBILICAL CABLE - INSTALLED

f. (AGM-12B) ORDNANCE SAFETY PLUG - INSTALLED

g. LIVE (ENGINE) IGNITOR -INSTALLED

ENSURE DUMMY IGNITOR IS REMOVED AND LIVE IGNITOR
INSTALLED.

h. (AGM-12C/E) BATTERY SWITCH PLUG - INSTALLED
I. (AGM—12C/E) ENGINE SAFETY SWITCH LEVER

LANYARD -CONNECTED TO BOMB RACK

4C-34-1-1-(143-2)

Figure 2-26 (Sheet 2 of 3)

Change 4

2-100 AC

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

AGM—12B/C/E MISSILE

(CONTINUED)

•—*

j. (AGM-12C/E) EJECTOR FEET NYLON PADS

- INSTALLED

Note

IF NYLON PADS ARE NOT INSTALLED,

THE AGM-12C/E MISSILE MAY EXPERIENCE
ERRATIC FLIGHT AFTER LAUNCH.

k. ENGINE -CLEAN NO LEAKS

l. MISSILE WINGS -SECURE

m. TRACKING FLARES - SECURE

Figure 2-26 (Sheet 3 of 3)

2-100AD

Change 4

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

20A/A BOMB ROCKET DISPENSER

IOC tear

AIMING

tOtlNOlO

INFLIGHT SAFETY LOCKOUT
BOLT & SAFETY PIN i

° PIN »°1

1 lVi

SUSPENSION EQUIPMENT

1. ARMAMENT PYLON -CHICK

a. PYLON SAFETY PIN - INSTALLED

EJECTOR CARTRIDGES - INSTALLED/REMOVED
INFLIGHT SAFETY LOCKOUT PIN - INSTALLED
LOCK INDICATOR - UNLOCKED
SWAY BRACES - TIGHTENED

Not#

WHEN ROCKETS ARE CARRIED IN THE SUU-20, JET¬
TISON CAPABILITY IS REQUIRED, THE EJECTOR CAR¬
TRIDGES MUST BE INSTALLED IN THE ARMAMFNT
PYLON, AND THE INFLIGHT LOCKOUT PIN (BOLT)
MUST BE INSTALLED. JETTISON IS ACCOMPLISHED
THROUGH THE MISSILE STATUS PANEL.

DISPENSER CHECK

1. BOMBS/ROCKET SAFETY CLIP -INSTALLED(RED FLAG)

2. BOMB AND ROCKET INTERVALOMETERS - SAFE
(PRECEDING SINGLE)

Nor*

ROTARY SELECTOR SWITCHES INSIDE

ACCESS DOOR-FWD

* * ♦

- BOMB/ROCKET INTERVALOMETER

INTERVALOMIITR

ROTATE THE INTERVALOMETER
CLOCKWISE ONLY.

3. (20/A) BOMB RETAINING LOCKS- INSTALLED (BDU-

33/B ONLY) '

4. (20A/A) EJECTOR GUN SAFETY PIN - INSTALLED

5. BOMBS - SECURE

6. ROCKETS SECURE,SEATED AGAINST FIRING PROBE

7. ROCKET FIN RETAINER - PLASTIC ONLY

4C-34-1-1—(145-1)

Figure 2-27 (Sheet 1 of 2)

Change 4

2-100AE

T.O. 1F-4C-34-1-1

INTERVALOMETERS

BOMB RETAINING ARMS

EJECTOR GUN SAFETY PIN

j P^SUU-20/A, & -20A/A BOMB R O C KE T DISPENSER
BOMB RETAINING ARM LOCKS SUU-20 A -—*

: BOMB RETAINING LOCKS]

RELEASE SEQUENCE

y.ii:

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

(gt AUTOMATIC @)

TOP VIEW

RELEASE SEQUENCE

SAFETY PINS (6)

■■■Hi

CIRCUIT E&PW BOMB
BREAKER^' | SEQUENCING

[ PRESS TO war J

MODE - / .
SWITCH I

SUSPENSION EQUIPMENT

1. ARMAMENT PYLON - CHECK

a. PYLON SAFETY PIN - INSTALLED

b. EJECTOR CARTRIDGES -REMOVED

c. INFLIGHT SAFETY LOCKOUT PIN -CHECK

(1) CONVENTIONAL WPNS MISSION - INSTALLED
(Z) DCU-94/A MISSION - NOT INSTALLED

d. LOCK INDICATOR -AS REQUIRED

e. SWAY BRACES - TIGHTENED

2. CENTERLINE RACK -CHECK

a. SAFETY PIN -INSTALLED (REMOVED PRIOR TO
ENGINE START)

b. EJECTOR CARTRIDGES -REMOVED

c. SWAY BRACES ON CENTERLINE ADAPTER - TIGHTENED

DISPENSER CHECK

THESE PROCEDURES ASSUME THAT THE DISPENSER DOORS
ARE OPEN

1. SAFETY PINS (6) - INSTALLED

2. RACK SWAY BRACES- SECURE

3. PRACTICE BOMBS - SECURE

4. BOMB SEQUENCING KNOB -AS REQUIRED

IF LESS THAN 6 BOMBS ARE INSTALLED, CHECK THAT
THE BOMB SEQUENCING KNOB IS SET ON THE PROPER
RELEASE SEQUENCE.

5. DISPENSER CIRCUIT BREAKER- IN

6. DISPENSER MODE SWITCH -MANUAL OR AUTOMATIC

7. ALL ACCESS PANELS -SECURE

4C-34—1—1—(*46)

Figure 2-28

Change 6

2-100AG

TmLEM'-^IT

T.O. 1F-4C-34-1-1

DART TARGET

GUIDE-IN SLOT

EXTERIOR INSPECTION

MODIFIED A/A 37U-15 TOW TARGET SYSTEM

[WFu-isTo w target system

swaybraces

MA-4 BOMB

RACK

■ targetbridu^hip
nyujnropeSB

GUIDE

INFLIGHT SAFETY LOCKOUT
BOLT & SAFETY PIN

INFLIGHT
LOCKOUT BOLT

SAFETY PIN
tOB «U£ CAST
A ,N£#S TO

SUSPENSION EQUIPMENT

★ 1. ARMAMENT PYLON EJECTOR CARTRIDGES - NOT

INSTALLED

★ 2. MA-4 BOMB RACK - LOCKED

★ 3. SWAYBRACE- IN PLACE & SECURE

★ 4. BALANCE WEIGHT GUIDE IN GUIDE SLOT.

5. ARMAMENT PYLON SAFETY PIN - INSTALLED

6. ARMAMENT PYLON SAFETY LOCK-OUT PIN (BOLT) -
INSTALLED

7. ARMAMENT PYLON LOCK INDICATOR - UNLOCKED
TARGET (TDU-IO/B)

★ 1 CABLE AND ROPE -SECURE WITH TAPE & LOCKWIRE
2. TARGET -NOT DAMAGED

★ SAFETY OF FLIGHT ITEMS

4C-34-1-1-OA7)

Figure 2-29

2-100AH

Change 4

FLARES

SHOfmNGCUP& FLARES'—

AERO 3/B LAUNCHER SAFETY PIN DOES NOT SAFE
LAUNCHER WHEN TDU-11B IS INSTALLED.

^ SHORTING CLIP -pS

Mrockctpict^^I

4C—34 — l — 1—(*48)

Figure 2-30

2-100 AJ

"AH data on pages 2-100AK thru 2-100AN deleted."

Change 4

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION

TDU-ll/b TARGET ROCKET 5-INCH HVAR

HVAR FIRING RECEPTACLE-,

1. LOAD CONFIGURATION- AS REQUIRED

2. ROCKET - SECURE

3. SHORTING CLIP -INSTALLED

4. PIGTAIL -TAPE TO LAUNCHER

5. TRACKING FLARES - SECURE

T.O. 1F-4C-34-1-1

PREFLIGHT

COCKPIT CHECK (BEFORE ELEC-PWR)

1. AF Form 781 - CHECK

2. Wing station jettison switch - NORMAL

The external wing tanks can be jettisoned by
the external wing tank jettison switch any
time electrical power is on the aircraft.

3. Internal wing dump switch - NORMAL

UTS/AWM-19

(UTS) AN/AWM-19 (F-4C/D/E)

CAUTION

With electrical power applied to the aircraft,
wing fuel will be dumped any time the internal
wing dump switch is in the DUMP position.

4. Gear handle - DOWN

5. Missile arm switch - SAFE

6. Master arm switch - SAFE

7. Generator switches - OFF

I CAUTION <|

Do not place the generator control switches
to EXT ON until external power has been
connected and has reached rated voltage and
frequency.

EXTERIOR INSPECTION

If the AN/AWM-19 umbilical test set is installed on
one or more of the missile stations, perform the fol¬
lowing checks:

1. Aero 7A launcher safety pin - INSTALLED
(figure 2-31).

2. Ejection squibs - REMOVED

3. Flag indicators - NO GO (All Black) (figure
2-32).

Figure 2-31

Figure 2-32

4. Motor fire connector connected to AN/AWM-19
(not missile motor).

Not*

If the flag indicators are tripped (white dots),
the UTS must be reset.

5. Station selector - AN/AWM-19 STATION (fig¬
ure 2-32)

6. Reset UTS if required.

a. Power applied to aircraft.

b. (P) Radar power - TEST

c. Missile select switch - RADAR

d. Missile power switch - STBY for 15 SEC

e. Missile power switch - PWR ON

f. After radar times in (30 sec) have crew
chief push AWM-19 reset button.

INTERIOR INSPECTION

Armament Area (Arming)

1. Armament switches - OFF or SAFE

2. Armament safety override button - PUSH IN

2-100AP

Change 7

T.O. 1F-4C-34-1-1

Note

Prior to the installation of ejector rack car¬
tridges, a stray voltage check is performed
by the armament crew. If the cartridges are
installed with the engines running, the AC
may push in the armament override button
when a stray voltage check is required. The
override button will pop out when the landing
gear handle is raised.

3. Aircrew - HANDS IN VIEW

The aircrew will place both hands in view as
a signal to the armament crew to approach
the aircraft. The armament crew may per¬
form a stray voltage check and install the
ejector cartridges. The crew will remove all
safety pins and install all access covers.

INFLIGHT

To use the UTS against a live target use same pro¬
cedures for launching a live missile as follows:

1. Missile arm switch - SAFE

2. Missile select switch - RADAR

3. Interlock switch - IN

4. (P) Radar power - OPR

5. (P) Gate switch - NAR

6. (P) Polar switch - LIN or CIR #1

7. (P) BIT checks - PERFORM

8. Missile power switch - STBY for 15 sec.

9. Missile power switch - PWR ON (select light
ON)

10. (P) Radar search and lock-on - ACCOMPLISH

11. Attack steering - ACCOMPLISH

12. Missile arm switch - ARM (READY light ON)

13. Obtain IN RANGE light and aim dot within ASE
circle.

14. Trigger switch - DEPRESS (Hold for 5 sec.)

15. Maintain tract to Break X or BREAK light.

Note

If more than one AWM-19 is loaded, repeat
steps 8 thru 14 for each illuminated set of
SELECT and READY lights.

16. Missile arm switch - SAFE

17. Missile power switch - OFF

Damage to the permanent magnet alternator
in the UTS may result if the missile power
switch is placed to OFF and then to PWR ON
in less than 5 seconds.

18. Repeat steps 8 thru 17 if second run is desired.

Change 1

2-100AQ

T.O. 1F-4C-34-1-1

BIT FIRING

1. (P) Radar power - TEST

2. Interlock switch - OUT

3. (P) Test switch - 6

4. (P) Obtain IN RANGE light.

Position the range strobe to an in- range posi¬
tion.

5. Missile power switch - STBY for 15 sec.

6. Missile power switch - PWR ON (Select light
ON)

7. Missile arm switch - ARM (Ready light ON)
Trigger switch - DEPRESS (Hold for 5 sec.)

Repeat step 8 for each set of illuminated Se¬
lect and Ready lights.

9. Missile arm switch - SAFE

10. Missile power switch - OFF

Damage to the permanent magnet alternator
in the UTS may result if the missile power
switch is placed to OFF and then to PWR ON
in less than 5 seconds.

Note

The following steps will be performed on the
fourth firing only.

11. (P) Test switch - 3

12. Gate switch - NAR

13. (P) Lock-on BIT target.

14. Missile power switch - STBY for 15 SEC.

15. Missile power switch - PWR ON (Select light

16 Missile arm switch - ARM (Ready light ON)

17 Trigger switch - DEPRESS (Hold for 5 sec.)

Repeat step 17 for each set of illuminated Se
lect and Ready lights.

18. Missile arm switch - SAFE

19. Missile power switch - OFF

before landing

1. Master arm switch - SAFE

2. Station select - OFF

3. Guns & stores switch - NORMAL (F-4D/E)

4. Sight Mode selector knob - STBY, or CAGE

(F-4D/E) x

5. All DCU-94/A station selector switches (o) -

AFT

6. Missile arm switch - SAFE

7. Missile power switch - OFF

8. Missile jett knob - OFF

ARMAMENT AREA (DE-ARMING)

1. Armament switches - OFF or SAFE

2. Aircrew - HANDS IN VIEW

RMU-8/A TOW TARGET SYSTEM (F-4C/D/E)

PREFLIGHT

COCKPIT CHECK (BEFORE ELEC PWR)

1. AF Form 781 - CHECK

2. Wing station jettison switch - NORMAL

I CAUTION 1

The external wing tanks can be jettisoned by
the external wing tank jettison switch any
time electrical power is on the aircraft.

3. Internal wing dump switch - NORMAL

CAUTION 1

With electrical power applied to the aircraft
wing fuel will be dumped any time the internal
wing dump switch is in the DUMP position.

CAUTION

Do not place the generator switches to EXT
ON until external power has been connected
and has reached rated voltage and frequency.

Tow system operation is performed by the tow sys¬
tem operator (TSO) from the rear cockpit. This
checklist covers those procedures to be followed by
the tow system operator and AC after the ground
crew has the tow system completely prepared for
flight. The checklist will be followed step by step
for all pre-operation and post-operation procedures.
Operational procedures and malfunction procedures
will be reviewed just prior to each operating se¬
quence, and should be referred to as required during
the sequence. Emergency procedures will be memo¬
rized and reviewed prior to each flight. Refer to the
Flight Manual for operating limitations of the air-
craft with the RMU-8/A Reel-Launcher and TDU-22
target installed.

Note

4. Gear handle - DOWN

5. Missile arm switch - SAFE

6. Master arm switch - SAFE

7. Generator switches - OFF

Procedural headings followed by TSO refer
to the tow system operator and those left
blank refer to the AC.

2-100AR

Change 1

T.O. 1F-4C-34-1-1

EXTERIOR INSPECTION (TSO) (FIGURE 2-33)

1. Target - SECURE

2. Target clamps - SNUG

3. Launcher - UP AND LOCKED

4. Towline length sensing unit - CHECK

a. Launch stop - SET AS REQUIRED

b. In stop - SET AS REQUIRED

c. Out stop - SET AS REQUIRED

d. Cable switch - OFF

5. N 2 pressure - 2000 to 3000 PSI

6. Auto-cut safety pin - REMOVED

Removing the auto-cut safety pin allows the
cutter arming switch to go to the spring loaded
arm position.

7. Turbine - CHECK

a. Condition of blades.

b. Blades feathered.

c. Brakes on.

WARNING

Turbine can reach 11,000 rpm in flight. Re¬
cord all nicks or scratches deeper than 0.001
inch on the RMU-8/A maintenance forms.

DO NOT operate reel-launcher until the dis¬
crepancy has been corrected and cleared for
flight by the RMU-8/A maintenance crew
chief.

8. All access panels - SECURED

9. Swaybraces - SECURE & SAFTIED

INTERIOR INSPECTION (TSO)

Before External Power is Connected

1. Tow system master switch - OFF

2. Emergency stop and cut switch guard - DOWN

(OFF)

3. No. 3 circuit breaker panel - CHECK

a. RMU-8/A EMER PWR circuit breaker (zone
10D) - IN

b. RMU-8/A PWR circuit breaker (zone 11D) -
IN

c. RMU-8/A circuit breaker (zone 12D) - IN

With External Power Connected

4. RMU-8/A 15 amp circuit breaker on indicator
panel - IN

5. Tow system master switch - ON

6. Test all tow system warning lights.

7. Check tow system warning lights.

All warning lights should be out with the ex¬
ception of the low oil pressure light.

8. Towline length counter - ZEROED

9. Towline speed indicator - ZERO

10. Towline tension - CHECK

Check for preload of approximately 200 to 400
pounds.

BEFORE TAXIING (TSO TO AC)

1. Tow system ready - MASTER SWITCH ON
(CALL)

INFLIGHT

TAKEOFF

1. Use normal operating procedures.

2. Towline tension - WITHIN LIMITS (1800
POUNDS MAX)

AFTER TAKEOFF-CLIMB

During Climb (TSO)

1. Towline tension - WITHIN LIMITS (1800
POUNDS MAX)

Note

The towline can be broken even with target
stowed. Tow operator will advise AC to re¬
duce airspeed and/or G if towline tension
becomes critical.

TOW SYSTEM OPERATION

An aircraft towing a cable is highly suscep¬
tible to being struck by lightening. Targets
should not be launched in the area of a
thunderstorm.

LAUNCHING TARGET

1. Maintain straight and level attitude.

2. Launch altitude - 15,000 - 20,000 FEET

3. Optimum airspeed - 300 KCAS

REEL-OUT

1. Permissable during climb to mission altitude
after the RMU-8/A reaches high speed reel-
out of 4775 to 5220 feet per minute.

2. Maximum airspeed - 320 KCAS

3. Maximum bank angle - 15 DEGREES

4. Maximum nose up attitude - 12 DEGREES

5. Maximum engine RPM during climb to mission
altitude - 95%

CRUISE

1. Maximum bank angle - 30 DEGREES

2. Airspeed should not exceed 350 KCAS

3. Normal airspeed - 300 KCAS

Note

If afterburner is required during a turn while
target is deployed, use outside afterburner
to prevent possibility of burning towline.
Maximum EGT on inboard engine is 500° dur¬
ing all turns.

Change 1

2-101

OD?S i i
VAUljCN STOP

02at»

IN STQP

i 6 6«

OUT STOP

NITROGEN
(N,) PRESSURE
GAUGE

UNLOCK

NITROGEN

SHUT-OFF

VALVE

CUTTER

AFT ACCESS
DOOR

TARGET LIMIT
SWITCH

ARMING SWITCH

TOWLINE LENGTH
SENSING UNIT

F4-34-II—413

LOW TENSION
SADDLE SHEAVE

CABLE

CUTTER _
CONNECTOR /

VIEW LOOKING
UP AND AFT

FORWARD
ACCESS DOOR

VIEW THRU FORWARD
ACCESS DOOR

Figure 2-33

2-102

Change 1

T.O. 1F-4C-34-1-1

LAUNCHING TARGET

TARGET DEPLOYMENT WITH LAUNCH STOP (TSO)

1. Launch/recover switch - LAUNCH TARGET

2. Launcher down light - ON

3. Target out light - ON

4. Towline tension - DECREASES TO ZERO

5. Towline length - INCREASING

6. Towline speed - 600 FPM MAXIMUM

7. Disregard low oil pressure light during launch.

After Passing Preset Launch Stop Setting

8. Launcher down light - OFF

9. Towline speed - DECREASING TO ZERO

10. Tow oil pressure light - ON

REEL-OUT (TSO)

After Reel Has Stopped -

11. Reel-out/Reel-in switch - REEL-OUT

Note

Launcher may recycle if lightweight target is
being used.

12. Towline length - INCREASING

13. Low oil pressure light - CHECK

Light should go out when towline speed in¬
creases to approximately 2500 fpm.

CAUTION

Low oil pressure light should be extinguished
prior to reaching a reel-out speed of 3500
fpm. If the light remains on as this speed is
approached, the TSO should initiate a normal
stop.

14. Cable tension - INCREASING

15. T£wline speed - 5250 FPM

'.Ttotfline reaches reel-out speed in 40 plus or
minus 5 seconds.

Note

Vibration may be noticable in the speed
governing range above 4775 fpm.

After Passing Preset Out-Stop

16. Towline speed - DECREASING TO ZERO

17. Low oil pressure light - CHECK

Light should illuminate when towline speed
decreases to approximately 2500 fpm.

Note

LAUNCHING TARGET

TARGET DEPLOYMENT UTILIZING DIRECT REEL-OUT
CYCLE (TSO)

1. Reel-out/Reel-in switch - REEL-OUT

2. Launcher down light - ON

3. Target out light - ON

4. Towline tension - DECREASES TO ZERO

5. Towline length - INCREASING

6. Towline speed - 600 FPM MAXIMUM

7. Disregard low oil pressure light during launch
cycle.

REEL-OUT

After Passing Preset Launch Stop Setting-

8. Launcher down light - OFF

9. Towline length - INCREASING

10. Towline speed - INCREASING

11. Low oil pressure light - CHECK

Light should go out when towline speed in¬
creases to approximately 2500 fpm.

If the low oil pressure light is not extin¬
guished when a towline speed of 3500 fpm is
reached, a normal stop should be initiated.

12. Cable tension - INCREASING

13. Towline speed - 5250 FPM MAXIMUM

After Passing Preset Out-Stop Setting

14. Towline speed - DECREASING TO ZERO

15. Low oil pressure light - ON

Low oil pressure light illuminates as the
towline speed reaches approximately 2500fpm

16. Towline speed - ZERO

Towline speed should read zero after approxi¬
mately 1800 feet of cable deployment after
passing through preset out-stop. See emer¬
gency procedures if reel fails to stop.

TDU-22 A/B TARGET FLARE IGNITION PROCEDURES

Note

The UHF radio in the rear cockpit is utilized
for flare ignition. The UHF frequency must
be set to the same frequency as the command
receiver in the target. A 10 second wait
period is required between each target com¬
mand transmission.

Target Flare Ignition Procedures (TSO)

Note

The target program relay must be stepped
from the safe to the ready position before
flare ignition can be accomplished. This
may be accomplished during reel-out.

See Emergency procedures if reel fails to
stop at preset out-stop setting.

2-103

T.O. 1F-4C-34-1-1

1. UHF command control light on UHF radio con¬
trol panel - ON

2. UHF radio frequency - SET AS REQUIRED

3. UHF channel mode select - MANUAL

4. UHF transmit receive selector - T/R+G

5. UHF mic button and flare tone button - DE¬
PRESSED FOR 5-10 SECONDS.

Depress both buttons simultaneously.

Note

The above procedure will be utilized for each
target command transmission. The target pro¬
gram relay has six positions for six com¬
mands. The sixth command will return the
relay to the safe position for target recovery.

REEL-IN (WITH TARGET)

1. Permissible during descent in a straight and
level flight, but not advisable during climb.

2. Maximum airspeed - 300 KCAS.

3. Optimum condition for descent is 250 KCAS to
an altitude of 15,000 feet.

4. A minimum reel-in speed of 3700 fpm should
be maintained by increasing airspeed or as ad¬
vised by TSO.

REEL-IN (TSO)

Note

Cable tension during reel-in should not ex¬
ceed 400 pounds less than the mission tension.

1. Reel-out/Reel-in switch - REEL-IN

2. Auto cut armed light - ON

3. Towline length - DECREASING

4. Low oil pressure light - CHECK

Light should go out when towline speed
reaches approximately 2500 fpm.

Note

If reel-in is with target attached, airspeed
should be adjusted to maintain a minimum of
3700 fpm towline speed to prevent illumina¬
tion of the low oil light.

5. Towline speed - 5250 FPM MAXIMUM

After Passing In-Stop Setting

6. Towline speed - DECREASING TO ZERO

TARGET RECOVERY

1. Permissable during straight and level flight

or a maximum bank angle of 5°. „„„

2. Maximum recommended airspeed - 300 KCAS
3'. Recommended recovery altitude - 15,000 FEET

a. Maximum recovery altitude - 20,000 FEET

b. Minimum recovery altitude - 10,000 FEET

TARGET RECOVERY (TSO)

1. Notify AC to establish flight conditions as brief
(300 KCAS, 15,000 feet altitude).

2. Launch/Recovery switch - RECOVER TARGET

3. Auto cut armed light - OFF

4. Launcher down light - ON

CAUTION

If a recovery is attempted directly after
launch, immediately key recovery speed
switch to INCREASE followed by actuation to
DECREASE.

5. Recovery speed switch - AS REQUIRED FOR
DESIRED RECOVERY RATE

Actuate recovery speed switch as required to
establish desired recovery rate (1100 fpm
maximum, about 5 actuations to move target).

6. Towline length - DECREASING

7. Disregard low oil pressure light during re¬
covery.

8. Towline speed - STABILIZED AT 150 FPM
PRIOR TO FINAL 50 FEET.

When Target Reaches Launcher

9. Target out light - OFF

10. Launcher down light - OFF

11. Towline tension - CHECK

Towline tension should be between 300 to 500
pounds.

12. Obtain confirmation from chase plane that
launcher is up and clamps are closed about
target.

13. Tow master switch - ON

Leave tow master switch on to monitor cable
tension for remainder of flight.

REEL-IN (WITH TARGET SHOT OFF)

1. Maintain 300 KCAS, and descend to an altitude
of 15,000 feet.

2. Reel-in of towline is accomplished during de¬
scent to final recovery altitude.

REEL-IN (WITH TARGET SHOT OFF) (TSO)

1. Utilize normal reel-in procedures.

Final Recovery of Tow Cable Without Target

1. Permissable during climb.

a. Maximum nose up attitude - 12 DEGREES

b. Maximum nose down attitude - 20 DEGREES

2. Maximum bank angle - 5 DEGREES

3. Optimum airspeed - 300 KCAS

4. If no chase plane is available, towline should
be cut after reel has stopped.

5. If chase plane is available, cable should be cut
when whipping or balling occurs or when cable
length is approximately 25 feet in length.

2-104

Towline Recovery (TSO)

1. Launch/recovery switch - RECOVER TARGET

2. Auto-cut armed light - OFF

3. Launcher down light - ON

4. Recovery speed switch - AS REQUIRED

5. Emergency stop and cut switch - STOP & CUT

Actuate emergency stop and cut switch on
command of chase plane.

6. Launcher down light - OUT

7. Towline speed - ZERO

8. Launcher up and tow cable cut, confirmed by
chase plane.

LANDING

1. Use normal procedures, and touch down be¬
yond arresting cable to preclude any chance of
target engaging the cable.

2. (TSO) Tow master switch - OFF

Turn tow master switch off after taxiing off
runway.

BEFORE LEAVING AIRCRAFT (TSO)

1. RMU-8/A discrepancies entered on applicable
forms.

2-105/(2-106 blank)

T.O. 1F-4C-34-1-1

SECTION III

EMERGENCY AIRCREW PROCEDURES

TABLE OF CONTENTS

PART 1.

Emergency Aircrew

PART 4. Emergency Aircrew

Procedures (F-4C) . . . .

... 3-3

Procedures (F-4C/D/E) ....

. 3-23

PART 2.

Emergency Aircrew
Procedures (F-4D) . . . .

... 3-9

Fire Fighting and Evacuation . .
RMU-8/A Tow Target Emer

. 3-23

PART 3.

Emergency Aircrew
Procedures (F-4E) . . . .

. . . 3-17

Procedures .

. 3-25

Change 8

3-l/(3-2 blank)

s->

T.O. 1F-4C-34-1-1

PART 1 EMERGENCY AIRCREW PROCEDURES

TABLE OF CONTENTS

EMERGENCY RELEASE PROCEDURES (F-4C). 3-3

Hung Ordnance.3-3

JETTISON PROCEDURES (F-4C).3-3

Emergency Jettison.. 3-3

Selective Jettison.3-4

EMERGENCY RELEASE PROCEDURES (F-4C)

Emergency Release is the term used when the normal
bomb release system is employed; e.g., to release
empty launchers or to expediently release weapons
with the ripple release mode. All non-nuclear, air-
to-ground weapons (with the exception of the gun pods
and AGM missiles) will be released through the nor¬
mal, non-nuclear weapons release mode. The sus¬
pension equipment should be retained during emer¬
gency conditions. Refer to jettison procedures when
TIME is the overriding factor.

HUNG ORDNANCE

Hung ordnance is the term used when an unsuccessful
attempt has been made to release or jettison aweapon
from the aircraft.

WARNING

FoHowing an attempted release or jettison,
any non-nuclear weapon that does not sepa¬
rate from the aircraft, the weapon should be
considered armed and susceptible to inadver¬
tent release during landing. Under these cir¬

cumstances, the aircrew should be prepared
to make an immediate go-around in the event
an inadvertent release of a hung store occurs
during landing.

EMERGENCY BOMB, LAUNCHER,

DISPENSER RELEASE

When an unsuccessful attempt has been made to re¬
lease the weapon(s) from the MER or TER, recheck
switch positions and repeat original release proce¬
dure. If weapon(s) release does not occur, perform
the following:

1. Home MER/TER bomb racks.

a. Weapons selector knob - RKTS & DISP

The above step is not required for launcher
and dispenser release.

2. Weapon selector knob - BOMB/RIPPLE

3. Arm nose-tail switch - SET AS REQUIRED

The SAFE position is normally used.

4. Bomb button - DEPRESS (hold 4 seconds)

5. Repeat the above procedure if all bombs do not
release.

6. If the weapon should not be returned to base,
refer to jettison procedures.

JETTISON PROCEDURES (F-4C)

WARNING

Refer to T.O. 1F-4C-1 (Unclassified) for mu¬
nition carriage and jettison restrictions on
the aircraft. Classified limitations are pro¬
vided in T.O. 1F-4C-34-1-1A.

The term jettison implies the use of the jettison con¬
trols or the normal release controls to clean the air¬
craft of suspension equipment, to launch missiles
unguided or to release the missiles without motor
ignition.

EMERGENCY JETTISON, MULTI¬
STATION

EXTERNAL STORE EMER RELEASE BUTTON

The external store emergency release button (panic
button) is the most expedient means to clean the wing
CL, and fuselage stations. The MAU-12 armament
pylons cannot be jettisoned; however, the MER and
TER, gun pods, AGM missiles (less the launcher),
and weapons suspended directly from the pylons are
jettisoned. Inboard wing mounted heat missiles or
the 5-inch HAVR target are jettison-launched by
motor ignition. Radar missiles are jettisoned.

Change 7

3-3

T.O. 1F-4C-34-1-1

WARNING

The AIM-9 missile should be considered
armed and to have some guidance capability.

The following conditions must exist:

a. Inflight lockout pins installed in the MAU-12
armament pylons. DCU-94/A LO, RO, LI, and RI
UNLOCKED lights illuminate.

b. (P) Emergency landing gear handle in or arma¬
ment safety override button pushed in.

c. Weight off the gear or landing handle in the up
position, or the armament safety override button
pushed in.

d. TK light on for the centerline station.

e. Wing flap switch full up for the wing station mis¬
siles.

f. For bombs suspended directly from the armament
pylons or a CL BRU-5Abomb rack, the master arm
switch or the arm nose tail switch must be in SAFE

if the bombs are to be jettisoned in the safe condition.

To jettison all external equipment, perform the fol¬
lowing:

1. Master arm switch - SAFE (if applicable)

2. External stores emergency release button
(panic button) - PUSH

SELECTIVE JETTISON

CENTERLINE STATION JETTISON

With the TK light ON, the equipment or weapon sus¬
pended from the BRU-5A bomb rack may be jetti¬
soned when the following conditions exist:

a. (WSO) Emergency landing gear handle in or arm¬
ament safety override button pushed in.

b. Weight off the gear or landing gear handle in the
up position.

To jettison the centerline suspension equipment or
store, perform the following:

1. Center station jettison switch - JETT.

AA118 and MK84 Jettison

The TK (tank aboard) light may provide an indica¬
tion of which jettison circuit is required to jettison

the M118 or MK 84 GP bomb from the CL bomb rack.
If the TK light is ON, the non-nuclear jettison circuit
can be used (the panic button or the centerline sta¬
tion jettison switch); the forward fuselage AIM-7
missiles cannot be launched.

If the TK light is OFF with the Ml 18 or MK 84 bomb
aboard, the centerline nuclear store jettison circuit
may be required to jettison the M118 or MK 84 bomb.

LEFT OR RIGHT INBOARD STATION JETTISON

The controls on the missile status panel are used to
jettison the left or right inboard station. With an
AGM-45A or AGM-12/B aboard, the missile is
jettisoned without motor ignition; the launcher re¬
mains aboard. The TER or single suspended weapons
are jettisoned. The rocket motor is ignited to jetti¬
son heat missiles and the TDU-ll/B target rocket.

All launchers remain aboard. The following condi¬
tions must exist to jettison from the armament pylon:

a. Inflight lockout pins installed, DCU-94/A LI and
RI UNLOCKED lights on.

b. Wing flap switch must be in the full UP position
to jettison the heat missiles or the target rocket.

c. For bombs suspended directly from the arma¬
ment pylons, the master arm switch must be in
SAFE if bombs are to be jettisoned in a safe condi¬
tion.

To jettison from the left or right inboard stations,
perform the following:

1. Master arm switch - SAFE (if applicable)

2. Missile jettison selector knob - L WING or
R WING

3. Missile jettison selector knob - PUSH

Note

The missile jettison selector knob is hot when
EXT or GEN power is applied to the aircraft.

OUTBOARD STATIONS JETTISON

(Before T.O. 1F-4-863)

The outboard station jettison switch receives power
as soon as EXT or GEN power is available. The
JETT position of the control jettisons the equipment
suspended on both outboard stations. Munitions sus¬
pended from the LAU-34 launcher are jettisoned with
the launcher retained.

3-4

Change 6

When bombs are suspended directly from the arma¬
ment pylon, the master arm switch or the arm/nose
tail switch must be in SAFE to preclude bomb arming.

OUTBOARD STATION JETTISON

(After T.O. 1F-4-863)

The outboard pylon jettison select switch (figure
3-1) provides a selective jettison function for the
outboard wing stations. The switch is positioned to
either LEFT, RIGHT, or BOTH, and then the wing
station jettison switch is energized to jettison the
contents of the outboard station(s). The selective
LEFT and RIGHT positions enable the AC to meet
specific jettison requirements if an unsymmetrical
external store load exists on the outboard stations.

Note

The outboard jettison selector is actually a
five-position switch and the UP and INBD
(unmarked) locations on the switch are OFF
positions. The (OFF) positions disable the
wing station jettison switch.

To jettison from the outboard stations perform the
following:

T.O. 1F-4C-34-1-1

ECM POD JETTISON

ECM pod equipment carried on wing and CL stations
would normally be jettisoned individually or collec¬
tively by using the controls described in the preced¬
ing paragraphs. However, T.O. 1F-4C-35 states thatl
ejector rack cartridges will not be installed in pylons I
with ECM equipment aboard. Fuselage mounted pods ^
cannot be jettisoned in any case; a fuselage station
jettison system does not exist when pods are aboard.

NUCLEAR JETTISON AND RELEASE CIRCUITS

The nuclear jettison and release circuits are func¬
tional through the DCU-94/A control-monitor panel
to jettison suspension equipment or weapons carried
by the wing station armament pylons (except the RO)
and the centerline station. With inflight lockout pins
installed in the wing armament pylons, the LO, RO,
LI and RI UNLOCKED lights on the DCU-94/A con¬
trol-monitor illuminate when power is applied to the
aircraft. If the nuclear jettison control is used to
jettison conventional stores, then the contents of all
nuclear stations (LO, LI, CL, RI) can be jettisoned
simultaneously or individually by selecting one or
more stations. If the nuclear release controls are
used, stations can only be jettisoned individually.

JETTISON THRU NUCLEAR RELEASE CIRCUIT

1. Outboard jettison selector (if available) -
LEFT, RIGHT, or BOTH

2. Wing station jettison switch - JETT

FUSELAGE MISSILE JETTISON

The controls on the missile status panel are used to
jettison the AIM-7 missiles from the forward and
rear fuselage stations (stations 3, 4, 6, and 7). The
missiles are selectively jettisoned without motor
ignition. When the TK light is ON, the two forward
missiles cannot be launched or jettisoned. The
missile jettison selector knob is hot with EXT or
GEN power applied to the aircraft.

1. Select the required fuselage station.

2. Missile jettison knob - PUSH

The DIRECT bombing mode and nuclear release con¬
trols may be used as an alternate method of jettison¬
ing the suspension equipment. However, the RO
MER cannot be released with the nuclear release
circuit and the LO MER can not be released when the
MER is shifted aft. The following procedures also
apply to bombs suspended directly from the arma¬
ment pylons or the centerline bomb rack.

Note

The inflight lockout pins may be IN or OUT.

1. Master arm switch - SAFE

With the master arm switch in SAFE, the
arm nose tail switch is inoperative. If single
suspended bombs are to be released ARMED,
place the master arm switch to ARM and the
arm nose tail switch to NOSE or NOSE &
TAIL.

Change 8

3-5

JETTISON CHART

kZJ

WING

STa

CENTER STA

LOCATION

SWITCH POSITION

SWITCH

STATION JETTISON

K» EXTERNAL
|»STORE$ EMER
RELEASE
(PANIC BUTTON)

LEFT SUB
PANEL

1. SELECT LEFT
RIGHT,

OR BOTH

LEFT/REAR

CONSOLE

E> OUTBDJETT
SELECT

E> WING STA
JETTISON
SWITCH

2. POSITION
UP TO
JETT

FUEL

CONTROL

PANEL

CENTER STA
JETTISON
SWITCH

POSITION

TO JETT

FUEL

CONTROL

PANEL

l> MISSILE
IfrjETTISON
KNOB

1. L WING
POSITION

2. PUSHTO
JETT

MISSILE

STATUS PANEL

E> MISSILE
EfrJETTISON
KNOB

1. R WING
POSITION

2. PUSHTO
JETT

MISSILE

STATUS PANEL

1. SELECT FUS.
STATION

2. PUSHTO
JETT

(REPEAT FOR
REMAINING
FUS. STATIONS)

Efr MISSILE
I>JETTISON
KNOB

MISSILE

STATUS PANEL

Notes

gffr After T.0.1F-4-863; the OFF position disables the wing sta
jett sw.

Control is HOT with EXT or GEN power ON.

Ffr Station 4 and 6 RDR missiles cannot jettison with fuel tank, MER,
or gun pod aboard CL station.

• See T.0.1F-4C-1 for jettison limits.

• Pylon inflight lockout pins must be installed.

• Fuselage ECM pods are non-jettisonahle; cartridges are not in
stalled in wing/CL stations with ECM pods aboard.

Emer gear handle IN with weight off gear or gear handle UP;
or arm safety override button IN.

Wing flap sw must be UP to jettison AIM—9 or TDU—11/B.

Figure 3-1 (Sheet 1 of 2)

3-6

Change 8

T.O. 1F-4C-34-1-1

JETTISON CHART

(CONTINUED)

DCU-94/A RELEASE

SWITCH

BOMB MODE SELECTOR KNOB

SWITCH POSITION

DIRECT

APPLICABLE STATION SELECTOR
SWITCH

FORWARD

MASTER RELEASE LOCK SWITCH

FORWARD

NUCLEAR STORE CONSENT SWITCH

REL OR REL/ARM

BOMB RELEASE BUTTON

DEPRESS

SELECTED STATION SELECTOR SWITCH.

(Repeot above procedures for
each station.)

AFT

Notes

1. The inflight lockout pins may or may not be installed.

2. RO station cannot be jettisoned thru DCU-94/A.

3. AIM-9B, AGM-12B and AGM-45 missiles cannot be jettisoned with the nuclear release circuit.

4C-34_l-l-(152-2)

Figure 3-1 (Sheet 2 of 2)

Change 6

3-7

T.O. 1F-4C-34-1-1

2. Bomb mode selector knob - DIRECT

The DIRECT mode provides an immediate
release when the bomb button is depressed.

3. DCU-94/A station selector switch - FORWARD
(DESIRED STATION)

4. DCU-94/A master release lock switch - FOR¬
WARD

a. DCU-94/A wing station UNLOCKED light
(if selected) - ON

Note

If the inflight lockout pins are not installed,
the wing station UNLOCKED light illuminates
after step 4. If the inflight lockout pins are
installed, these lights illuminate continuously.

5. (P) Nuclear store consent switch - REL or
REL/ARM

a. DCU-94/A CL UNLOCKED light (if the CL
station is selected) - ON

6. Bomb button - DEPRESS

The suspension equipment or the single sus¬
pended bomb on the selected station is re¬
leased when the bomb button is depressed.

7. For remaining station(s), place the station
selector AFT and repeat steps 3 and 6.

Jettison with Nuclear Jettison Circuit

CAUTION I

DAMMAM

The nuclear store jettison circuit should not
be used for selective jettison from a particu¬
lar station. The nuclear store jettison button
(NUCLEAR PUSH TO JETT) should be used
as a last resort, and only when the inadver¬
tent jettison from unselected stations is of
little concern. For example, the fuselage
missiles may be jettisoned and both inboard
stations may be jettisoned even though only

the right or left inboard station is selected on
the DCU-94/A. Both outboard stations may
be jettisoned even though only the left outboard
station is selected on the DCU-94/A. When
only the centerline station is selected, only
the centerline station is jettisoned. When
only the RO station is selected, the nuclear
jettison circuit is inoperative.

The following procedures apply for bombs and MER/
TER's that are suspended directly from the arma¬
ment pylon or the BRU-5/A centerline bomb rack:

Note

The inflight lockout pins may be IN or OUT.

1. Master arm switch - SAFE (if applicable)

With the master arm switch in SAFE, the
arm nose tail switch is inoperative. If single |
suspended bombs are to be released ARMED, |
place the master arm switch to ARM and the
arm nose tail switch to NOSE or NOSE &

TAIL.

2. DCU-94/A station selector switches (loaded
stations) - FORWARD

3. DCU-94/A master release lock switch - FOR¬
WARD

a. DCU-94/A wing station UNLOCKED lights
(if selected) - ON

If the inflight lockout pins are not installed,
the wing station UNLOCKED lights illumi¬
nate after step 3. If the flight lockout pins
are installed, these lights illuminate con¬
tinuously with power on the aircraft.

4. (P) Nuclear store consent switch - REL or
REL/ARM

a. DCU-94/A CL UNLOCKED light, if the CL
station is selected - ON

5. Nuclear store jettison switch - JETT

The selected stations jettison simultaneously.!

3-8

Change 6

T.O. 1F-4C-34-1-1

PART 2

EMERGENCY AIRCREW PROCEDURES

TABLE OF CONTENTS

EMERGENCY RELEASE PROCEDURES

(F-4D). 3-9

Hung Ordnance. 3-9

JETTISON PROCEDURES (F-4D). 3-9

Emergency Jettison.. 3-9

Selective Jettison.. 3-10

EMERGENCY RELEASE PROCEDURES (F-4D)

Emergency Release is the term used when the normal
bomb release system is employed; e.g., to release
empty launchers or to expediently release weapons
with the ripple release mode. All nonnuclear, air-
to-ground weapons (with the exception of the gun pods
and AGM missiles) will be released through the nor¬
mal, non-nuclear weapons release mode. The sus¬
pension equipment should be retained during emer¬
gency conditions. Refer to jettison procedures when
TIME is the overriding factor.

HUNG ORDNANCE

immediate go-around in the event an inad¬
vertent release of a hung store occurs dur¬
ing landing.

EMERGENCY BOMB, LAUNCHER, DISPENSER
RELEASE

When an unsuccessful attempt has been made to re¬
lease the weapon(s) from the MER or TER, recheck
switch positions and repeat original release proce¬
dure. If weapon(s) does not release, perform the
following:

Hung ordnance is the term used when an unsuccessful
attempt lias been made to release or jettison aweapon
from the aircraft.

WARNING

Following an attempted release or jettison,
any nonnuclear weapon that does not sepa¬
rate from the aircraft should be considered
armed and susceptible to inadvertent release
during landing. Under these circumstances,
the aircrew should be prepared to make an

1. Home MER/TER bomb racks.

a. Weapons selector knob - RKTS & DISP

The above step is not required for launcher
and dispenser release.

2. Weapons selector knob - BOMB/RIPPLE.

3. Arm nose-tail switch - SET AS REQUIRED

The SAFE position is normally used.

4. Bomb button - DEPRESS (hold 4 seconds)

5. Repeat the above procedure if all bombs do not
release.

6. If the weapon should not be returned to base,
refer to jettison procedures.

JETTISON PR0CEDURES(F-4D)

WARNING

Refer to T.O. 1F-4C-1 (Unclassified) for
carriage and jettison restrictions on the air¬
craft. Classified limitations are provided in
T.O. 1F-4C-34-1-1A.

The term jettison implies the use of the jettison con¬
trols or the normal release controls to clean the air¬
craft of suspension equipment, to launch missiles
unguided, or to release the missiles without motor
ignition.

EMERGENCY JETTISON, MULTI¬
STATION

CL, and fuselage stations. The MAU-12 armament
pylons cannot be jettisoned. However, the MER's
and TER's, gun pods, AGM missiles (less the launch¬
er), and weapons suspended directlyfrom the pylons
are jettisoned. With the centerline tank aboard (TK)
light ON, a MK 84 or Ml 18 GP bomb, the centerline
MER, fuel tank, or gun pod is jettisoned from the
BRU-5A bomb rack. AIM-9 and AIM-4D missiles
cannot be jettisoned. (See figure 3-2). Radar mis¬
siles are jettisoned.

WARNING

EXTERNAL STORE EMER RELEASE BUTTON

The external store emergency release button (panic The AIM-9 missile should be considered

button) is the most expedient means to clean die wing armed and to have some guidance capability.

Change 7

3-9

T.O. 1F-4C-

The following conditions must exist:

a Inflight lockout pins installed in the MAU-12 ar¬
mament pylons. DCU-94/A LO, LI, and RI UN¬
LOCKED lights illuminate.

b. (WSO) Emergency landing gear handle in or arma¬
ment safety override button pushed in.

c. Weight off the gear or landing handle in the up
position, or the armament safety o'verride button
pushed in.

d. TK light on for the centerline station.

e. Wing flaps must be up for wing station AIM-9
missiles.

f. For bombs suspended directly from the arma¬
ment pylons or the BRU-5A bomb rack, the master
arm switch or the arm nose tail switch must be in
SAFE if the bombs are to be jettisoned in the safe
condition.

To jettison all external equipment, perform the fol¬
lowing:

1. Master arm switch - SAFE (if applicable)

2. External stores emergency release button
(panic button) - PUSH

SELECTIVE JETTISON

CENTERLINE STATION JETTISON

When the TK light is ON the tank aboard relay is en¬
ergized, the equipment or weapon suspended from
the BRU-5/A bomb rack is jettisoned when the fol¬
lowing conditions exist:

a. (WSO) Emergency landing gear handle in or arma¬
ment safety override button pushed in.

b. Weight off the gear or landing gear handle in the
up position.

To jettison the centerline suspension equipment or
store, perform the following:

1. Center station jettison switch - JETT.

Note

If the TK is OFF with the Ml 18 or MK 84 bomb
aboard, the nuclear store jettison circuit may be re¬
quired to jettison the Ml 18 or MK 84 bomb. On F-
4D-28 and up, the tank aboard relay is bypassed (TK
light is OFF) when the gun pod is aboard; therefore,
the two forward AIM-7 missiles can be launched.

LEFT OR RIGHT INBOARD STATION JETTISON

The controls on the missile status panel are used to
jettison the left or right inboard station. The arma¬
ment pylon inflight lockout pins must be installed.

The TER or single suspended weapons are jettisoned.
The rocket motor is ignited to jettison the heat mis¬
siles and the TDU-ll/B target rocket. The heat
missiles are not armed and have no hydraulic power
for guidance. The AGM-45 and AGM-12B/C missiles
are jettisoned without motor ignition and the LAU-
34/A launcher remains with the pylon. The following
conditions must exist to jettison from the inboard
armament pylon:

a. Inflight lockout pins installed, DCU-94/A LI and
RI Unlocked lights on.

b. The emergency landing gear handle must be IN
and the weight off the gear, or landing gear handle
UP, or armament safety override button IN.

c. To jettison the AIM-4D and AIM-9 missiles, the
wing flaps and the landing gear must be up. For the
AIM-4D, the left main gear door must be closed. For
the AIM-9, weight must be off the left main gear.

d. For bombs suspended directly from the arma¬
ment pylons, the master arm switch must be in
SAFE if the bombs are to be jettisoned in a safe con¬
dition.

To jettison from the left or right inboard stations
perform the following:

1. Master arm switch - SAFE (if applicable)

2. Missile jettison selector knob - L WING or
R WING

3. Missile jettison selector knob - PUSH

F-4D-28 and up, the TK light is OFF when
the gun pod is loaded on the CL station.

However, the gun pod can still be jettisoned
with the center station jettison switch.

Mil8 AND MK 84 JETTISON

The TK (tank aboard) light may provide an indication
of which jettison circuit is required to jettison the
M118 or MK 84 GP bomb from the BRU-5A bomb
rack. If the TK light is ON, the non-nuclear jettison
circuit can be used (the panic button or the centerline
station jettison switch): the forward fuselage radar
missile cannot be launched.

OUTBOARD STATIONS JETTISON (Before T.O. 1F-4
-863)

The outboard station jettison switch receives power
as soon as EXT or GEN power is available. The JETT
position of the control jettisons the equipment sus¬
pended on both outboard stations. Munitions sus¬
pended from the LAU-34 launcher are jettisoned with
the launcher retained. When bombs are suspended
directly from the armament pylon, the master arm
switch or the arm/nose tail switch must be in SAFE
to preclude bomb arming. The AGM-12B is jettisoned
without motor ignition; the launcher remains aboard.

3-10

Change 8

T.O. 1F-4C-34-1-1

OUTBOARD STATIONS JETTISON (After T.O. IF-4-

863)

The outboard pylon jettison select switch (figure 3-2)
provides a selective jettison function for the outboard
wing stations. The switch is positioned to either
LEFT, RIGHT, or BOTH, and then the wing station
jettison switch is energized to jettison the contents of
the outboard station(s). The selective LEFT and
RIGHT positions enable the AC to meet specific jet¬
tison requirements if an unsymmetrical external
store load exists on the outboard stations.

Note

The outboard jettison selector is actually a
five-position switch and the UP and INBD
(unmarked) locations on the switch are OFF
positions. These positions disable the wing
station jettison switch.

To jettison munitions from the outboard stations per¬
form the following:

1. Outboard jettison selector (if available) - LEFT,
RIGHT, or BOTH.

2. Wing station jettison switch - JETT

FUSELAGE MISSILE JETTISON

The controls on the missile status panel are used to
jettison the AIM-7 missiles from the forward and
rear fuselage stations (stations 3, 4, 6, and 7). The
missiles are selectively jettisoned without motor
ignition. When the TK light is ON, the two forward
missiles cannot be launched or jettisoned. The emer¬
gency landing gear handle must be IN and the weight
off the gear, or landing gear handle UP, or arma¬
ment safety override button IN. To jettison a radar
missile, perform the following:

1. Select the required fuselage station.

2. Missile jettison selector - PUSH

ECM POD JETTISON

ECM pod equipment carried on wing and CL stations
would normally be jettisoned individually or collec¬
tively by using the controls described in the preced¬
ing paragraphs. However, T.O. 1F-4C-35 states that
ejector rack cartridges will not be installed in pylons
with ECM equipment aboard. Fuselage mounted pods
cannot be jettisoned in any case; a fuselage station
jettison system does not exist when pods are aboard.

ECM Jettison Switch

The ECM jettison switch on the left console is func¬
tional only if an ECM pod is aboard the RO station (9)
and only if RO rack cartridges are installed. This
control will not jettison a station 9 munition or fuel
tank.

NUCLEAR JETTISON AND RELEASE CIRCUITS

The nuclear jettison and release circuits are func¬
tional through the DCU-94/A control-monitor panel

to jettison suspension equipment or weapons that are
carried by the armament pylons (except the RO) and
the centerline bomb rack. When the inflight lockout
pin is installed in the wing armament pylons, the LO,
LI and RI UNLOCKED lights on the DCU-94/A con¬
trol-monitor illuminate with EXT or GEN power ap¬
plied to the aircraft.

If the nuclear jettison control is used to jettison con¬
ventional stores, then the contents of all nuclear
stations (LO, LI, CL, RI) can be jettisoned simul¬
taneously or individually by selecting one or more
stations. If the nuclear release controls are used,
stations can only be jettisoned individually.

Jettison Thru Nuclear Release Circuit

The DIRECT bombing mode and nuclear release con¬
trols may be used as an alternate method of jettison¬
ing the suspension equipment. However, theRO MER
cannot be bombed off with the nuclear release circuit
and the LO MER cannot be bombed off when the MER
is shifted aft. The following procedures also apply
for bombs that are suspended directly from the arma¬
ment pylons or the centerline bomb rack.

Note

The inflight lockout pins may be IN or OUT.

1. Master arm switch - SAFE

With the master arm switch in SAFE, the arm
nose tail switch is inoperative. The master
arm switch is used only with single bomb sus¬
pension. If the bombs are to be released
ARMED, place the master arm switch to
ARM and the arm nose tail switch to NOSE or
NOSE & TAIL.

2. Bomb mode selector knob - DIRECT

The DIRECT mode is used to provide an im¬
mediate release when the bomb button is de¬
pressed.

3. DCU-94/A station selector switch - FORWARD
(DESIRED STATION)

4. DCU-94/A master release lock switch - FOR¬
WARD

a. DCU-94/A wing station UNLOCKED light
(if selected) - ON

Note

If the inflight lockout pins are not installed,
the wing station UNLOCKED light illumi¬
nates after step 4. If the inflight lockoutpins
are installed, these lights illuminate contin¬
uously.

5. (WSO) Nuclear store consent switch - REL or
REL/ARM

a. DCU-94/A CL UNLOCKED light (if the CL
station is selected) - ON

6. Bomb button - DEPRESS

The suspension equipment or the single sus¬
pended bomb on the selected station is re¬
leased when the bomb buttofi is depressed.

7. For remaining station(s), place the station se¬
lector AFT and repeat steps 3 and 6.

Change 8

3-11

EXT STORES
EMER REL

SWITCH POSITION

SWITCH

STATION JETTISON

|» EXTERNAL
E> STORES
EMER
RELEASE

(PANIC BUTTON)

LEFT SUB
PANEL

ALL STATIONS

1. SELECT LEFT,
RIGHT
OR BOTH

LEFT/REAR

CONSOLE

E> OUTBDJETT
SELECT

2. POSITION
UP TO
JETT

WING STA
JETTISON
SWITCH

FUEL

CONTROL

PANEL

OUTBOARD STATIONS

E» CENTER STA
JETTISON
SWITCH

POSITION
UP TO
JETT

FUEL

CONTROL

PANEL

••••••

CENTERLINE STATION

1. L WING
POSITION

MISSILE

JETTISON

KNOB

MISSILE

STATUS PANEL

2. PUSH
CENTER
BUTTON

LEFT INBOARD STATION

1. R WING
POSITION

|» MISSILE
JETTISON
KNOB

MISSILE

STATUS PANEL

2. PUSH
CENTER
BUTTON

RIGHT INBOARD STATION

1. SELECT FUS
STATION

2. PUSH
CENTER
BUTTON

MISSILE
i» JETTISON
D KNOB

MISSILE

STATUS PANEL

FUSELAGE MISSILES

Notes

• See T.0.1F-4C-1 tor jettison limits.

• Pylon inflight lockout pins must be installed.

• Fuselage ECM pods are non-Jettisonable; cartridges are not
installed in wing/CL stations with ECM pods aboard.

Enter gear handle IN with weight oft gear or gear handle UP; or
armament safety override button IN.

Heat missiles do not jettison

After T.0. 1 F- 4 - 863 ;the OFF position disables the wing sta
jett sw.

Switch is HOT with EXT. or GEN. power ON.

Wing flaps must be UP to jettison heat missiles; gear UP for
AIM-40.

Station 4 and G RDR missiles cannot jettison with fuel tank, MER,
or gun pod aboard CL station. (Block 28 and up, CL gun pod will
not inhibit station 4 and 6 jettison.)

4C-34-1-M 153-2)

Figure 3-2 (Sheet 1 of 2)

3-12

Change 8

JETTISON CHART )f-4D\

(CONTINUED) DCU-94/A RELEASE

T.O. 1F-4C-34-1-1

STATION JETTISON

SWITCH

SWITCH POSITION

RELEASE

DELIVERY MODE SELECTOR KNOB

APPLICABLE STATION SELECTOR
SWITCH

MASTER RELEASE LOCK SWITCH

NUCLEAR STORE CONSENT SWITCH

BOMB RELEASE BUTTON

DIRECT

FORWARD

RELORREL/ARM

DEPRESS

SELECTED STATION SELECTOR SWITCH.

(Repeat above procedures for
each station.)

AFT

Notes

1. The inflight lockout pins may or may not be installed.

2. RO station cannot be jettisoned thru DCU-94/A.

3. AGM-12B, AGM-45 and heat missiles can not be jettisoned.

4C—34— 1— 1—< 153—3)

Figure 3-2 (Sheet 2 of 2)

"AH data on page 3-14 deleted."

Change 6

3-13/(3-14 blank)

T.O. 1F-4C-34-1-1

Jettison with the Nuclear Jettison Circuit

{caution 1

The nuclear store jettison circuit should not
be used for selective jettison from a parti¬
cular station. The nuclear store jettison but¬
ton (NUCLEAR PUSH TO JETT) should be
used only after all other jettison methods
have failed or can not be used, and only when
the inadvertent jettison from unselected sta¬
tions is of little concern. For example; the
fuselage missiles may be jettisoned and both
inboard stations will be jettisoned even
though only the right or left inboard station
is selected on the DCU-94/A. Both outboard
stations may be jettisoned even though only
the left outboard station is selected on the
DCU-94/A. When only the centerline station
is selected, only the centerline station will
be jettisoned. When only the RO station is
selected, the nuclear jettison circuit is inop¬
erative.

The following procedures apply for bombs and MER/
TER's suspended directly from the armament pylon
or the centerline bomb rack:

Note

The inflight lockout pins may be IN or OUT.

1. Master arm switch - SAFE (if applicable)

With the master arm switch in SAFE, the
arm nose tail switch is inoperative. The
master arm switch is used only with single
bomb suspension. If the bombs are to be re¬
leased ARMED, place the master arm switch
to ARM and the arm nose tail switch to NOSE
or NOSE & TAIL. The AIM-4D missile and
the launchers cannot be jettisoned with the
nuclear jettison circuit.

2. DCU-94/A station selector switches (loaded
stations) - FORWARD

3. DCU-94/A master release lock switch - FOR¬
WARD

a. DCU-94/A wing station UNLOCKED lights
(if selected) - ON

If the inflight lockout pins are not installed,
the wing station UNLOCKED lights illumi¬
nate after step 3. If the flight lockout pins
are installed, these lights illuminate while
power is on the aircraft.

4. (P) Nuclear store consent switch - REL or
REL/ARM

a. DCU-94/A CL UNLOCKED light, if the CL
station is selected - ON

5. Nuclear store jettison button - PUSH

3-15/(3-16 blank)

T.O. 1F-4C-34-1-1

PART 3 EMERGENCY AIRCREW PROCEDURES

F-4E

TABLE OF CONTENTS JETTISON PROCEDURES (F-4E). 3-17

Emergency Jettison. 3-17

EMERGENCY RELEASE PROCEDURES Selective Jettison. 3-18

(F-4E) Hung Ordnance. 3-17

EMERGENCY RELEASE AND JETTISON PROCEDURES IF-4EJ

BEFORE T.O. 1F-4E-556

Emergency Release is the term used when the normal
bomb release system is employed; e.g. to release
empty launchers or to expediently release weapons
with the ripple release mode. All nonnuclear, air-
to-ground weapons (with the exception of the gun pods
and AGM missiles) may be released through the nor¬
mal, nonnuclear weapons release mode. The sus¬
pension equipment should be retained during emer¬
gency conditions. Refer to jettison procedures when
TIME is the overriding factor.

HUNG ORDNANCE

Hung ordnance is the term used when an unsuccess¬
ful attempt has been made to release or jettison a
weapon from the aircraft.

Following an attempted release or jettison,
any non-nuclear weapon that does not sepa¬
rate from the aircraft should be considered
armed and susceptible to inadvertent release
during landing. Under these circumstances,
the aircrew should be prepared to make an
immediate go-around in the event an inad¬
vertent release of a hung store occurs during
landing.

EMERGENCY RELEASE (BOMBS,
LAUNCHERS & DISPENSERS)

1. Home MER/TER bomb racks.

a. Weapons selector knob - RKTS & DISP
The above step is not required for launcher
and dispenser release.

2. Weapons selector knob - BOMB/RIPPLE.

3. Arm nose tail switch - SET AS REQUIRED

The SAFE position is normally used.

4. Bomb button - DEPRESS (hold 4 seconds)

5. Repeat the above procedure if all bombs do not
release.

6. If the weapon should not be returned to base,
refer to jettison procedures.

Refer to T.O. 1F-4C-1 (Unclassifed) for
flight and jettison restrictions.

The term jettison implies the use of the jettison con¬
trols or tiie normal release controls to clean the air¬
craft of suspension equipment, to launch missiles
unguided, or to release the missiles without motor
ignition.

EMERGENCY JETTISON, MULTI¬
STATION

EXTERNAL STORE EMER RELEASE BUTTON

The external store emergency release button (panic
button) is the most expedient means to clean the air¬
craft. The MAU-12 armament pylons cannot be jet¬
tisoned. However, the MER's and TER's, gun pods,
AGM missiles (less the launcher), and weapons sus¬
pended directly from the pylons are jettisoned through
this control. The heat and radar missiles are not
jettisoned.

The following conditions must exist:

a. Inflight lockout pins installed in the MAU-12
armament pylons. DCU-94/A LO, LI, and RI UN¬
LOCKED lights illuminate.

b. (WSO) Emergency landing gear handle in or arma¬
ment safety override button pushed in.

c. Weight off the gear or landing handle in the up
position, or the armament safety override button
pushed in.

d. TK light on for the centerline station.

e. For bombs suspended directly from the arma¬
ment pylons or the BRU-5A bomb rack, the master
arm switch or the arm nose tail switch must be in
SAFE if the bombs are to be jettisoned in the safe
condition.

To jettison wing and CL station external equipment,
perform the following:

1. Master arm switch - SAFE (if applicable)

2. External stores emergency release button
(panic button) - PUSH

Change 8

3-17

T.O. 1F-4C-34-1-1

SELECTIVE JETTISON

CENTERLINE STATION JETTISON

a. (WSO) Emergency landing gear handle in or arma¬
ment safety override button pushed in.

b. Weight off the gear or landing gear handle in the
up position.

c. TK light - ON.

To jettison the centerline suspension equipment or
store, perform the following:

1. Center station jettison switch - JETT.

Note

The TK light is OFF when the gun pod is
loaded on the CL station. However, the gun
pod can still be jettisoned with the center
station jettison switch.

M118 and MK 84 Jettison

The TK (tank aboard) light may provide an indication
of which jettison circuit is required to jettison the
M118 or MK 84 GP bomb from the BRU-5A bomb
rack. If the TK light is ON, the conventional weapons
jettison circuit can be used (the panic button or the
centerline station jettison switch); the forward fuse¬
lage AIM-7 missiles cannot be launched.

If the TK is OFF with the M118 or MK 84 bomb
aboard, the nuclear store jettison circuit may be re¬
quired to jettison the Ml 18 or MK 84 bomb. The
tank aboard relay is bypassed (TK light is OFF) when
the gun pod is aboard; therefore, the two forward
AIM-7 missiles can be launched with the gun pod
aboard and then the bomb and the gun pod can be
jettisoned with the non-nuclear jettison circuit.

LEFT OR RIGHT INBOARD STATION JETTISON

The controls on the missile status panel are used to
jettison the left or right inboard station. Position
the missile jettison selector knob to L WING or to
R WING and then push the missile jettison knob.

The inflight lockout pin must be installed in the MAU-
12 armament pylons. The pylons cannot be jettisoned.
The TER's or single suspended weapons will be jet¬
tisoned. The rocket motor must be ignited to jettison
the heat missiles. The AIM-4D and AIM-9 are not
armed and will not have hydraulic power for guid¬
ance. The AGM-45 and AGM-12B/C missiles are
jettisoned without motor ignition and the LAU-34/A
launcher remains on the pylon. The following condi¬
tions must exist to jettison from the MAU-12 arma¬
ment pylon:

a. Inflight lockout pins installed, DCU-94/A LI and
■RI UNLOCKED lights on.

b. Wing flaps must be up to jettison heat missiles.

c. The emergency landing gear handle must be in
and weight off the landing gear, or landing gear han¬
dle up; or armament safety override button in. For
the AIM-4D, the left main gear door must be closed.
For the AIM-9, the weight must be off the left main
gear.

d. For bombs suspended directly from the arma¬
ment pylons, the master arm switch or the arm nose
tail switch must be in SAFE if the bombs are to be
jettisoned safe.

To jettison from the left or right inboard stations,
perform the following:

1. Master arm switch - SAFE (if applicable)

2. Missile jettison selector knob - L WING or
R WING

3. Missile jettison selector knob - PUSH

OUTBOARD STATIONS JETTISON

Both outboard wing stations are jettisoned when the
wing station jettison switch is placed to JETT; the
switch is "hot" when power is applied to the aircraft.
The inflight lockout pins must be installed. The RO
UNLOCKED light will not be illuminated. When
bombs are suspended directly from the armament
pylon, the master arm switch must be in SAFE to
preclude bomb arming. The AGM-12B is jettisoned
without motor ignition; the launcher remains aboard.

To jettison from the outboax-d stations, perform the
following:

1. Master arm switch - SAFE (if applicable)

2. Wing station jettison switch - JETT

FUSELAGE MISSILE JETTISON

The controls on the missile status panel are used to
jettison the AIM-7 missiles fi’om the foi-ward and
aft fuselage stations (stations 3, 4, 6, and 7). The
missiles will be jettisoned without motor ignition.

Note the following conditions:

a. When the TK lights is ON, the two forward mis¬
siles cannot be launched or jettisoned. Refer to BRU
5A bomb x'ack, section I.

b. The emergency landing gear handle must be IN
with weight off the gear, or landing gear handle UP,
or armament safety override button in.

c. Missile jettison selector button - PUSH

ECM POD JETTISON

ECM pod equipment carried on wing and CL stations
would normally be jettisoned individually or collec¬
tively by using the controls described in the preced¬
ing paragraphs. However, T.O. 1F-4C-35 states that
ejector rack cartridges will not be installed in pylons
with ECM equipment aboard. Fuselage mounted pods
cannot be jettisoned in any case; a fuselage station
jettison system does not exist when pods are aboard.

ECM Jettison Switch

3-18

Change 8

T.O. 1F-4C-34-1-1

EMERGENCY RELEASE AND JETTISON PROCEDURES
|F-4E| AFTER T.O. 1F-4E-556

This part of emergency release and jettison data is
presented essentially in the form of difference data.
Therefore terms such as hung ordnance, or the re¬
lease interlocks such as the landing gear handle are
not redefined since they are the same as described
in the preceding pages.

EMERGENCY RELEASE (BOMBS,
LAUNCHERS & DISPENSERS)

These procedures consider the emergency release of
bombs, dispensers, or rocket launchers using the
normal release controls (figure 3-3, sheet 2). The
procedure may be used when weapons are to be emer¬
gency-released without the loss of carriage equip¬
ment (MERS or TERS). The weapon select BOMBS
position is used, and the arm nose tail switch must
be out of the SAFE position to get the indications of
the station ARM light. It is assumed that release
systems controls are already energized; the AC has
the DIRECT mode, master arm, and the desired
stations selected.

jettisoned if AIM-4 or AIM-9 munitions are aboard,
and fuselage missile stations are not jettisoned. The
munitions, including MER/TER carriage equipment
are jettisoned directly from the armament pylon (fig¬
ure 3-3 sheet 2). If the LAU-34 launcher is aboard
(AGM-45, AGM-12B) the launcher is retained.

EMERGENCY JETTISON,

SELECTIVE STATIONS

The selective jettison control on the main instrument
panel may be used to jettison the contents of any con¬
ventional store station on the aircraft. This includes
any wing and CL station stores, inboard wing station
heat missile, and fuselage station radar missiles.

HEAT MISSILES (STATIONS 2 AND 8)

Heat missile stations 2 and 8 are selected individually
by positions L WING or R WING, and both missiles
aboard that station are jettisoned by depressing the
PUSH TO JETT control. The missiles are launched
ballistically (motor ignited) in an inert state.

1. Weapon selector knob - BOMBS

Select BOMBS if RKTS & DISP were previ¬
ously selected.

2. ARM nose tail switch - OUT OF SAFE

With BOMBS selected, the arm nose tail
switch must be in an (ON) position to obtain
the station ARM light ON.

3. AWRU Qty knob - C or S

The C or S positions provide the most rapid
release method.

When selecting either C or S, observe mini¬
mum release interval between bombs released
from the same aircraft station.

4. Bomb button - DEPRESS

a. Hold bomb button signal until station ARM
lights go off.

If all munitions do not release:

AGM-65/A MISSILES (STATIONS 2 AND 8)(71-237
and up)

The AGM-65/A (Maverick) missiles are individuaUy
jettisoned by using the same switching procedures as
those used for heat missiles. The difference is that
a single missile is jettison-launched when the JETT
button is depressed. The entire load (missiles plus
LAU-88/A launcher) is jettisoned by following the
procedures for Wing and CL Stations (below).

RADAR MISSILES (STATIONS 3, 4, 6, AND 7)

Fuselage station radar missiles are jettisoned indi¬
vidually by selecting either L FWD, R FWD, L AFT,
or R AFT, and depressing PUSH TO JETT. A single
radar missile is ejected and f reef alls without motor
ignition.

5. Weapon selector knob - RKTS & DISP

6. Weapon selector knob - BOMBS

7. Bomb button - DEPRESS

a. Station ARM lights - OFF

If munitions do not release, refer to jettison proce¬
dures.

EMERGENCY JETTISON, MULTI-STATION

EXTERNAL STORES EMERGENCY RELEASE BUTTON

The external stores emergency release button may
be used to jettison simultaneously toe contents of
stations 1, 2, 5, 8 and 9. Stations 2 and 8 are not

WING AND CL STORES (STATIONS 1, 2, 5, 8 AND 9)

The AC selects the STORES position on the jettison
knob and depresses the required station select but¬
tons) for the station(s) to be jettisoned. The cor¬
responding stores are jettisoned by depressing the
PUSH TO JETT button. If heat missiles are aboard,
stations 2 and 8 do not jettison.

NUCLEAR JETTISON AND RELEASE
CIRCUITS (ALL AIRCRAFT)

The nuclear circuits are functional through the DCU-
94/A control-monitor panel to jettison suspension

Change 7

3-19

T.O. 1F-4C-34-1-1

equipment or weapons carried by the MAU-12 arma¬
ment pylons (except the RO) and the centerline BRU-
5A bomb rack. When the inflight lockout pin is in¬
stalled in the wing armament pylons the LO, LI and
RI UNLOCKED lights on the DCU-94/A control-
monitor illuminate when power is applied to the air¬
craft. The RO light will not illuminate even though
the pin may be installed.

CAUTION I
I

Nuclear jettison controls are considered
here only as a backup method if all other
methods have failed or cannot be used, i.e.,
inflight lockout pins not installed. With con¬
ventional weapons aboard, nuclear j ettison
procedures may not yield the desired results.

When the inflight lockout pins are installed, the non¬
nuclear jettison circuit can be used to jettison the
MER's and TER's from the armament pylons. If the
inflight lockout pins are not installed, only the nuclear
store circuit can be used to jettison the LO, LI and
RI stations; the RO station cannot be jettisoned. When
the nuclear circuits are used, the UNLOCKED lights
illuminate after the DCU-94/A master release lock
switch is positioned forward and the DCU-94/A sta¬
tions are selected, regardless of the nuclear store
consent switch; however, the nuclear store consent
switch must be in REL or REL/ARM before the LO
MER or TER’s can be jettisoned. The DCU-94/A CL
UNLOCKED lights will not illuminate until all three
switches are energized.

a. DCU-94/A CL station selector - FORWARD

b. DCU-94/A Master release lock switch - FOR¬
WARD

c. Nuclear store consent switch - REL or REL/
ARM

JETTISON WITH THE NUCLEAR RELEASE CIRCUIT

The bomb release button, the DCU-94/A control-
monitor, the DIRECT bombing mode, and nuclear
store consent switch may be used as an alternate
method of jettisoning the suspension equipment. How¬
ever, the LO MER when shifted aft and the RO MER
cannot be bombed off with nuclear release circuit.
The following procedures also apply for bombs that
are suspended directly from the armament pylons or
the centerline bomb rack.

Note

Inflight lockout pins - IN or OUT

1. Master arm switch - SAFE

With the master arm switch in SAFE, the arm
nose tail switch is inoperative. The master
arm switch is used only with single bomb sus¬
pension. If the bombs are to be released
ARMED, place the master arm switch to ARM
and the arm nose tail switch to NOSE or NOSE
& TAIL. The heat missiles and the launchers
cannot be released with the nuclear release
circuit.

2. Delivery mode selector knob - DIRECT

The DIRECT mode is used to provide an im¬
mediate release when the bomb button is de¬
pressed.

3. DCU-94/A station selector switch - FORWARD
(DESIRED STATION)

4. DCU-94/A master release lock switch - FOR¬
WARD

a. DCU-94/A wing station UNLOCKED light (if
selected) - ON

Note

If the inflight lockout pins are not installed,
the wing station UNLOCKED light illuminates
after step 4. If the inflict lockout pins are
installed, these lights illuminate continuously.

5. (P) Nuclear store consent switch - REL or
REL/ARM

a. DCU-94/A CL UNLOCKED light (if the CL
station is selected) - ON

6. Bomb button - DEPRESS

The suspension equipment or the single sus¬
pended bomb on the selected station will be
released when the bomb button is depressed.

7. For remaining station(s), place the station
selector AFT and repeat steps 3 and 6.

JETTISON WITH THE NUCLEAR JETTISON CIRCUIT

The following procedures apply to bombs and MER/
TER's that are suspended directly from the arma¬
ment pylon or the centerline bomb rack:

3-20

Change 5

T.O. 1F-4C-34-1-1

emerrei

x —* RESET
AIR REFUEL i

_£j

WING

STA

^. -CENTER STA

BEFORE T.O. 1F-4E-556

STATION JETTISON

JETTISON CONTROL

I * EXTERNAL
STORES
EMERGENCY
RELEASE

(PANIC BUTTON)

MULTI-STATION

WING

l> STATION
JETTISON
SWITCH

OUTBOARD STATIONS

CENTERLINE

STATION

JETTISON

SWITCH

CENTERLINE STATION

LEFT INBOARD STATION

RADAR MISSILES

Notes

i» MISSILE
JETTISON

KNOB

1. L WING
POSITION -

2. PUSH

CENTER

BUTTON

MISSILE

STATUS PANEL

» MISSILE
JETTISON

KNOB

1. R WING

POSITION -

2. PUSH

CENTER

BUTTON

MISSILE

STATUS PANEL

■> MISSILE

JETTISON
(ONE STATION
CONSIDERED)

1. SELECT FUS.
STATION

2. PUSH TO JETT

MISSILE

STATUS

PANEL

JETT. PROCEDURE

LOCATION

PUSH

LEFT SUB
PANEL

POSITION

TO JETT

FUEL

CONTROL

PANEL

POSITION

TO JETT

FUEL

CONTROL

PANEL

• See T.O. 1F-4C-1 for jettison limits.

• Pylon inflight lockout pins must be installed.

• Fuselage ECM pods are non-jettisonable; cartridges are not in¬
stalled inwing/CL stations with ECM pods aboard.

D Emer gear handle IN with weight off gear or gear handle UP;
or armament safety override button IN.

E> Heat and RDR missiles do not jettison.

Switch is HOT with EXT or GEN or GEN power ON.

Wing flaps must be UP to jett heat missiles; gear UP for AIM-40
& Station 4 and 6 RDR missiles cannot jett with fuel tank or MER
aboard CL station.

4C-34- 1 —1—(154-1)

Figure 3-3 (Sheet 1 of 3)

Change 8

3-20A

T.O. 1F-4C-34-1-1

pps.

JETTISON CHART J

F-4E

(CONTINUED)

AFTER T.O. 1F-4E-556

MULTI-STATION JETTISON

JETTISON CONTROL

EXTERNAL
STORES
EMERGENCY
RELEASE
(PANIC BUTTON)

JETT PROCEDURE

LOCATION

PUSH

LEFT SUB
PANEL

RADAR MISSILES

WING & CL STORES

STOfit

L At l

STATION

1. Depress de—

SELECT

sired stat ion(s)

BUTTON(S)

(CL station

considered).

SELECTIVE

2. Select stores.

JETTISON

3. PUSH TO JETT

E»

D Heat and RDR missiles do not jettison
Wing flaps must he up. This procedure
jettisons a single AGM-65 missile.

Station 4 and 6 RDR missiles cannot jettison
with fuel tank or MER aboard the CL station.
rV Heat missiles will not jettison.

Notes

• For all jettison, emer gear handle must be IN with
weight off left main gear or the landing gear must
be UP; or Arm Safety Override button pushed IN.

• Pylon inflight lockout pins must be installed.

• Fuselage ECM pods are non-jettisonable; car¬
tridges are not installed in wing/CL stations
with ECM pods aboard.

• Refer to T.O. 1F-4C-1 for jettison limitations.

Figure 3-3 (Sheet 2 of 3)

3-20B

Change 8

T.O. 1F-4C-34-1-1

JETTISON CHART

(CONTINUED)

DCU-94/A RELEASE

STATION JETTISON

SWITCH POSITION

1. The inflight lockout pins may or may not be installed.

2. RO station can not be jettisoned.

3. AGM-12B, AGM-45, and Heat missiles can not be jettisoned.

4C-34-1-1-(154-3)

Figure 3-3 (Sheet 3 of 3)

Change 5

T.O. 1F-4C-34-1-1

Note

The inflight lockout pins may be IN or OUT.

1. Master arm switch - SAFE (if applicable)

With the master arm switch in SAFE, the arm
nose tail switch is inoperative. The master
arm switch is used only with single bomb sus¬
pension. If the bombs are to be released
ARMED, place the master arm switch to ARM
and the arm nose tail switch to NOSE or NOSE
& TAIL. The AIM-4D missile and the launch¬
ers cannot be jettisoned with the nuclear jet¬
tison circuit.

2. DC U-94/A station selector switches (loaded
stations) - FORWARD

3. DC U-94/A master release lock switch - FOR¬
WARD

a. DCU-94/A wing station UNLOCKED lights
(if selected) - ON

4. (P) Nuclear store consent switch - REL or
REL/ARM

a. DCU-94/A CL UNLOCKED light, if the CL
station is selected - ON

5. Nuclear store jettison button - PUSH

3-22

T.O. 1F-4C-34-1-1

PART 4 EMERGENCY AIRCREW PROCEDURES

TABLE OF CONTENTS

FIRE FIGHTING AND EVACUATION. ... 3-23

Timer Factor and Evaluation Criteria . . 3-24

RMU-8/A TOW TARGET SYSTEM EMER¬
GENCY PROCEDURES . 3-25

Ejection. 3-25

Barrier Engagement. 3-25

Reel Overspeed. 3-25

Excessive Vibration. 3-25

Tow System Emergency Power Light

Illumination. 3 -25

Tow System High Oil Temperature Light
Illumination. 3-25

Tow System Low Oil Pressure Light

Illumination. 3-26

Tow System Low Air Light Illumination. . 3-26

Target Out Light Illuminated with Target

Stowed. 3-26

Launcher Fails to Latch on Recovery. . . 3-26

Towline Failure. 3-26

Reel Fails to Stop At Preset Stop .... 3-26

Target Shot OFF. 3-27

Hazardous Release Conditions (See T.O.
1F-4C-34-1-1A, Sec. HI).

FIRE FIGHTING AND EVACUATION

These emergency procedures consist of actions to be
taken if munitions are involved in a fire. The air¬
crew should be thoroughly familiar with these pro¬
cedures. Refer to T.O. 11A-1-55 for fire fighting
information.

In event of a fire enveloping munitions, it is impera¬
tive that the time the fire envelops a munition be
recorded. This action is required to determine time
left to evacuate the area prior to munitions function.

The following table gives the withdrawal time in
minutes and withdrawal distance in feet. At the ex¬
piration of the time factor in the table, the munition
may be expected to function. The aircrew should
withdraw to specified distance within applicable time
limits after fire envelops munitions or after arrival
of fire fighters, whichever occurs first. NA (Not
Applicable) indicates that time or distance is not a
factor.

Change 5

3-23

TIME FACTOR AND EVACUATION DISTANCE CRITERIA

NOMENCLATURE

WITHDRAWAL TIME
IN MINUTES

WITHDRAWAL DISTANCE IN FEET
FOR NONESSENTIAL PERSONNEL

All Fire Bombs.

Flares, Markers and Practice Bombs:
SUU-20, -21, -25, -42 Series; LUU-l/B,
-2/B, -5/B, -6/B; MK 24 Mod 4; BDU-
33 and MK106

Leaflet Bombs M129E1, E2
Incendiary Cluster Bomb M36E2
Ejector Rack Cartridges
20mm Cartridges T.P. (Ball)

Dispenser and Bomb CBU-9 Series
20mm Cartridges HEI, API
GP Bomb with M1A1 Fuze Extender
Dispenser and Mine CBU-33/A, CBU-34
Series, and CBU-42/A
Cluster Bomb, Anti-Tank, MK 20 Mod 2

Spray Tanks:

A/B45Y-1 and A/B45Y-4
TMU-28/B

A/B45Y-2 NA

PAU-7/A NA

Dispensers and Bombs:

CBU-1A/A, CBU-2, CBU-7A/A, 1.5

CBU-12, CBU-24, CBU-29,

CBU-30/A, CBU-38, CBU-46/A,

CBU-49, CBU-52A/B, CBU-58,

CBU-70, SUU-41 Loaded,

Rockeye II

Gas Bomb MC-1 5.0

Chemical Bombs BLU-52/B, A/B NA

Guided Weapons:

MK 1 Mod 0, 2, 6 and 7 (Walleye) 5.0

Bomb/Destructor:

BLU-31, KMU-351, KMU-353, KMU- 5.0

I 370, KMU-388, KMU-390, M117, M117D,

Ml 18, MK36, MK82, MK83, MK84

2 Miles Downwind

Personnel must remain clear of the area to the fore and aft of rockets
and missiles during firefighting and evacuation.

Rockets:

2.75 Inch (All Warheads)

2.5

2000

5 Inch HVAR, Target, TDU-ll/B

2.5

2000

Missiles:

AGM-12B

1.75

2000

AGM-12C, E

2.5

2000

AGM-45A

1.0

2000

AIM-4D-8, -7D, E, E2, -9B, E

1.0

2000

3-24

Change 8

T.O. 1F-4C-34-1-1

RMU-8/A TOW TARGET SYSTEM
EMERGENCY PROCEDURES

The emergency procedures described herein are for
emergency operation of the F-4C, F-4D, and F-4E
aircraft with the tow system installed. These proce¬
dures represent changes and additions to the basic
aircraft emergency procedures for purposes of emer¬
gency operation with the tow system.

Note

Procedural headings followed by TSO refer to
the tow system operator and those left blank
refer to the AC.

EJECTION

EJECTION (AC)

1. Advise TSO of ejection and obtain immediate
acknowledgement that target is stowed or tow-
line is cut.

2. Continue with established ejection procedures.

EJECTION (TSO)

When Advised by AC to Eject, Immediately

1. Cut the towline unless target is stowed.

2. Call ’’towline cut" or "target stowed".

3. Continue with established ejection procedures.

BARRIER ENGAGEMENT (TSO)

1. Do not jettison target on runway.

REEL OVERSPEED (TSO)

If Reel Speed Exceeds 5500 FPM (Matching Control
Panels with Reel)

1. Advise AC to slow aircraft to minimum safe
flying speed.

2. Normal stop switch - ACTUATE

Allow reel to come to a complete stop.

3. Reel-in and recover target.

If Reel Exceeds 6000 FPM

1. Advise AC to rapidly reduce airspeed to a mini¬
mum safe flying speed and lower landing gear
when airspeed is below 250 KCAS. The nose
gear will tend to spoil the airflow to the tur¬
bine.

2. Emergency stop and cut switch - ACTUATE

3. Be prepared to jettison reel if turbine begins
to disintegrate.

4. If turbine speed is controlled below 6000 FPM,
land as soon as possible. If available, request
escort aircraft to maintain visual confirmation
of reel condition.

EXCESSIVE VIBRATION (TSO)

1. Excessive vibration could occur due to aircraft
or tow reel malfunctions. If reel is not operat¬
ing, do not take any action until advised by AC.

2. If excessive vibration occurs during launch or
reel-out, actuate normal stop switch and allow
reel to stop. If vibration ceases as reel slows
down, the level wind is probably out of synchro¬
nization. Recover target and terminate mission.

3. If vibration occurs during reel-in or recovery
and continues after normal stop has been ac¬
complished, the difficulty is probably in the
aircraft. Target should be immediately re¬
covered or cable cut as directed by AC.

TOW SYSTEM EMERGENCY POWER
LIGHT ILLUMINATED (TSO)

Note

The emergency power light is illuminated if
normal aircraft power is momentarily inter¬
rupted. During operation with emergency
power, all normal functioning of the system is
automatically stopped and control switches are
inoperative except the emergency stop and cut
switch. If reel is in operation a normal stop
is automatically initiated. To resume normal
operation, the tow master switch must be cy-
cycled to OFF and back to ON.

1. If reel is in operation, wait for reel to stop.

2. Tow master switch - OFF

3. If RMU-8/A circuit breaker(s) on No. 3 circuit
breaker panel has popped - RESET

4. Tow master switch - ON

5. If normal power is restored, continue mission.

If Normal Aircraft Power Cannot Be Restored

6. Tow master switch - ON

7. Emergency stop and cut switch - ACTUATE

^"uTION j

If circuit breaker(s) pop twice, reset emer¬
gency power circuit breaker, and actuate
emergency stop and cut switch.

TOW SYSTEM HIGH OIL TEMPERATURE
LIGHT ILLUMINATED (TSO)

1. Normal stop switch - ACTUATE

2. Wait 10 minutes.

3. High oil temperature light - OUT

4. Continue mission.

3-25

Note

T.O. 1F-4C-34-1-1

5. If high oil temperature light and low oil pres¬
sure light come on simultaneously during reel-
out or reel-in, actuate emergency stop and cut
switch.

TOW SYSTEM LOW OIL PRESSURE
LIGHT ILLUMINATED (TSO)

Note

This light may be illuminated during launch
and recovery, and will be on until reel speed
reaches about 2500 fpm during reel-out or
reel-in.

1. If light fails to go out at 3500 fpm during reel-
out, actuate normal stop switch.

2. If light fails to go out at 3500 fpm during reel-
in, immediately actuate emergency stop and cut
switch.

TOW SYSTEM LOW AIR LIGHT
ILLUMINATED (TSO)

1. If light illuminates prior to launch, do not at¬
tempt to operate system. Terminate mission
and land as soon as practicable.

2. If light illuminates after several reel cycles,
recover target.

If Light Illuminates For No Apparent Reason

3. If launcher is lowered, make every possible at¬
tempt to recover target because pressure may
not be available to retract launcher if towline is
cut or broken.

TARGET OUT LIGHT ILLUMINATED WITH
TARGET STOWED (TSO)

1. Advise AC to reduce airspeed to minimum safe
flight speed.

2. Obtain visual confirmation from another air¬
craft if possible.

3. Advise AC to land as soon as practicable using
a straight-in approach.

LAUNCHER FAILS TO LATCH AT LAUNCH
STOP (TSO)

1. Advise AC to stay below minimum launcher
down speed (475 KCAS or 0.9 Mach, whichever
is lower).

2. Normal stop switch - ACTUATE

Launcher should retract and lock up.

If Launcher is Still Reported Down by Chase Plane

'■ 3. Reel-out/reel-in switch - REEL-OUT

4. Normal stop switch actuates after approximately
1000 feet of cable is reeled out.

5. Launch/recover switch - RECOVER TARGET

6. Normal stop switch - ACTUATE

3-26

Steps 5 and 6 recycle the launcher. If light
goes out or chase plane reports launcher full
up, continue mission. If launcher down light
stays illuminated or chase plane reports
launcher hanging, recover target and terminate
mission. Air pressure may be depleted if
mission is continued.

LAUNCHER FAILS TO LATCH ON
RECOVERY (TSO)

1. Recovery speed switch - INCREASE

f CAUTION {

Do not exceed towline leader breathing strength

2. If target light is out and launcher down light is
illuminated, perform the following steps at 3
second intervals:

a. Launch/recovery switch- LAUNCH TARGET

b. Normal stop switch - ACTUATE

This will cycle the launcher.

3. If chase plane reports target in clamps in nor¬
mal locked position, advise AC to proceed with
straight in approach landing.

4. If no chase plane is available or chase plane re¬
ports target below clamps or lodged in clamps,
perform the following steps:

a. Normal stop switch - ACTUATED

b. Tow master switch cycled - OFF THEN ON

c. Launch/recovery switch - RECOVER TAR¬
GET

d. Recovery speed switch - INCREASE (MAXI¬
MUM)

e. Increase airspeed - 300 KCAS

f. If launcher does not latch, actuate emer¬
gency stop and cut switch.

5. If launcher fails to latch, advise AC to perform
a normal landing with launcher down. Launcher
will clear runway during landing. The TSO
should request ground crew to meet the aircraft
when taxiing from runway to lock the launcher
up.

TOWLINE FAILURE (TSO)

1. If towline failure occurs during the launch or
reel-out cycle, actuate the emergency stop and
cut switch.

REEL FAILS TO STOP AT A PRESET STOP
(TSO)

Note

If reel fails to stop or decelerate, or towline
speed stabilizes below normal operating
range, the difficulty is probably the accelera¬
tion monitor system or a defective pitch
change actuator. The following steps should
be performed in 5 second intervals.

T.O. 1F-4C-34-1-1

REEL FAILS TO STOP AT PRESET OUT-STOP

1. Advise AC to slow aircraft to a minimum safe
flying speed.

2. Normal stop switch - ACTUATED

3. RMU-8/A 15 amp circuit breaker on indicator
panel - PULL OUT

This step places the system on emergency
power.

4. RMU-8/A 5 amp circuit breaker on No. 3 cir¬
cuit breaker panel (zone D12) - PULL OUT

Pulling this circuit breaker, deactivates the
speed monitor system.

If No Decrease In Towline Speed (FPAA) is Noted After
Performing the Preceding Steps

5. Tow reel master switch - OFF

Placing the tow master switch to OFF sets the
turbine brake.

6. Allow reel to come to a complete stop.

7. Obtain conformation of turbine position from
chase plane.

8. If chase plane reports turbine blades to be in
reel-out position, reset 15 amp RMU-8/A cir¬
cuit breaker on indicator panel.

9. Tow master switch - ON

10. If blades do not feather, actuate normal stop
switch.

11. Reel-in/reel-out switch - REEL-IN

12. When towline speed indicator reads zero fpm,
actuate normal stop switch.

13. Reset 5 amp circuit breaker on No. 3 circuit
breaker panel (zone D12).

14. Continue mission.

Note

Auto cut armed light will remain on.

REEL FAILS TO STOP AT PRESET IN-STOP

Due to small amount of towline, the following
steps should be performed at 3 second inter¬
vals or until there is a definite decrease in
towline speed or until reel has completely
stopped.

1. Normal stop switch - ACTUATE

2. Advise AC to slow aircraft to minimum safe
flying speed.

3. RMU-8/A 15 amp circuit breaker on indicator
panel - PULL OUT

4. RMU-8/A 5 amp circuit breaker on No. 3 cir¬
cuit breaker panel (zone D12) - PULL OUT

5. Tow reel master switch - OFF

After Reel Has Stopped

6. Obtain confirmation from chase plane of turbine
position.

7. If chase plane confirms turbine blades in
feather position, reset all circuit breakers and
continue normal recovery procedures.

8. If chase plane reports the turbine blades in a
reel-in angle, reset 15 amp circuit breaker on
RMU-8/A indicator panel.

9. Tow master switch - ON

10. If turbine blades are not feathered, actuate
normal stop switch.

11. Reel-in/reel-out switch - REEL-OUT

12. When towline speed indicator reads zero fpm,
actuate normal stop switch.

13. RMU-8/A 5 amp circuit breaker on No. 3 cir¬
cuit breaker panel (zone D12) - RESET-IN

14. Continue with normal recovery procedures.

TARGET SHOT OFF (AC-TSO)

1. Normal procedures are utilized for cable re¬
covery (300 KCAS descent to recovery altitude
of 15,000 to 20,000 feet).

TARGET SHOT OFF (TSO)

1. Reel-out/reel-in switch - REEL-IN

2. After passing preset in-stop and reel has
stopped, if no chase plane is available, actuate
emergency stop and cut switch.

3. After the reel has stopped after passing preset
in-stop and chase plane is available, perform
the following procedures:

a. Launch/recovery switch - RECOVER TAR¬
GET

b. Utilize normal recovery procedures.

c. Actuate emergency stop and cut switch when
chase plane advises of excessive whipping or
balling or when cable length reaches 25 feet
in length.

FLARE IGNITION DURING TAXIING OR
ENGINE START

When utilizing TDU-22A/B with TAU-15B in¬
frared flares, pre-flare ignition may occur
during engine start or taxiing.

Flare Ignition During Engine Start or Taxiing (AC)

1. Expedite engine start and prepare for imme¬
diate taxi of aircraft.

2. Taxi aircraft from parking and stop when ad¬
vised by TSO.

3. If flare ignition occurs in route to runway, ex¬
pedite taxi.

Flare Ignition During Engine Start or Taxiing (TSO)

1. When advised by ground crew that flares have
ignited and all personnel are clear of the
launcher assembly, the following procedures
should be followed:

a. Tow master switch - ON

b. Launch/recovery switch - LAUNCH TARGET

c. Emergency stop and cut switch - ACTUATE

d. Advise AC to expedite taxi of aircraft.

3-27

3-28

T.O. 1F-4C-34-1-1

SECTION IV

* '1

SUPPLEMENTARY DATA

TABLE OF CONTENTS

Safe Separation Data. .......... 4-1

Error Analysis...4-4

Harmonization of Aircraft and Guns .... 4-7

WRCS Operational Envelope.. 4-9

CTU-l/A Release Stability.4-12

SAFE SEPARATION DATA

Mil7; MK 82, 83 LDGP; AND
MC-1 BOMBS

The release conditions listed in the bombing tables
for these items provide a minimum of 100 feet AGL
recovery altitude. The 100-foot minimum altitude
is based on a 4.0 G pullout acceleration with 4.0 G
obtained in 2.0 seconds after the stated release al¬
titude. Based on studies of data available to date,
the minimum release altitudes listed in the Fuzing
and Safe Escape Charts should provide safe escape
from the bomb fragments for all contact burst and
airburst (VT fuze) situations.

BLU-31/B LAND MINE

WARNING

• When the FMU-30/B fuze is used with the
BLU-31/B land mine, minimum release al¬
titudes which provide safe escape from bomb
fragments for instantaneous or contact bursts
shall be selected. This is required to pro¬
tect the aircraft and aircrew in the event of
premature bomb detonation at initial impact.

Refer to Safe Escape, figure 6-14.

•For BLU-31/B land mine shapes, the tra¬
jectory angle at impact shall be in excess of
15° to preclude ricochet.

The land mine with the FMU-30/B Fuze has been
successfully tested for impact velocities up to 900
ft/sec. Release conditions which result in impact
velocities of 900 ft/sec or less should be selected
during mission planning. Refer to section VI, MLU-
10/B and BLU-31/B Impact Velocity tables, T.O. 1F-
4C-34-1-2.

(No ricochet data are available for the BDU-33/B
practice bombs.)

2.75” FFAR

Based on limited data available from static firing,
the minimum launch altitudes listed in section VI,
Safe Escape, may be used. If the rockets are launched
above these altitudes, the aircraft should not pene¬
trate the fragment envelope during the assumed 4.0
G (in 2.0 sec) pullout. Refer to the Safe Escape
chart, figure 6-14.

MAXIMUM FRAGMENT ENVELOPE
CHARTS

The Maximum Fragment Envelope charts figure 4-1
show the fragment position relative to the weapon
burst point as a function of time, and are used in de¬
termining the safe release interval between aircraft
during multiple aircraft attacks. The charts are
based on the assumption that the most hazardous
fragment (i.e., the heaviest fragment with the maxi¬
mum velocity) can be projected from the burst point
at any angle, irrespective of weapon delivery condi¬
tions. Similar charts for 2.75-inch rockets are given
as a function of impact angle where the impact angle
is approximately equal to the aircraft dive angle. The
rocket envelopes may be rotated for consideration of
launch angles other than those given.

SUMMARY

Additional and more detailed bomb and rocket frag¬
mentation data will be included in this publication as
studies and tests are completed by the Ballistics
Division, Directorate of Armament Division, Eglin
AFB, Fla. during Project 9088, Aircraft/Munitions
Safe Separation Evaluation. The bomb and rocket re¬
lease conditions will be changed to include new mini¬
mum conditions as they are determined.

"All data on page 4-2 deleted"

Change 1

4-1/(4-2 blank)

.AA/ tW*

ALTITUDE - FEET ALTITUDE - FEET

(1 UNIT = 100 Feet) (1 UNIT = 100 Feet)

MAXIMUM FRAGMENT ENVELOPE

FRAGMENTATION DATA ESTIMATED
FROM TRITONAL LOADED Ml 17 BOMB.

TIME IN SECONDS IS GIVEN
ADJACENT TO EACH DATA POINT.

-1000 0 1000
HORIZONTAL RANGE - FEET (1 UNIT = 100 FEET)

MK-82 LDGP BOMB

TIME IN SECONDS IS GIVEN
ADJACENT TO EACH DATA POINT.

HORIZONTAL RANGE - FEET (1 UNIT = 100 FEET)

MK-83 & MK-84 LDGP BOMBS

} TIME IN SECONDS IS GIVEN

ADJACENT TO EACH DATA POINT.

■

-1000 0 1000
HORIZONTAL RANGE - FEET (1 UNIT = 100 FEET)

Figure 4-1 (Sheet 1 of 3)

Change 1

pxj

:52nd

t7pj-

± z J± :

■ ■■■■■'

B 5

4?fi -

7 j 9

1 3

‘ - ' • .5

7-1

44+r

•r-’-r.

9 <

i :<

'/ ■

1 /

!S » /

..4T~ I

. . .

\\ faFfc

—>

-Hi

itfc

-IS

42;

I r 5

—

- _—_

—

— 1 -T—- J -

ALTITUDE - FEET ALTITUDE - FEET ALTITUDE - FEET

(1 UNIT = 50 Feet) (1 UNIT - 50 Feet) (1 UNIT = 50 Feet)

„Xj

. . •

L 14-1

—

liiHi %

>00

MAXIMUM FRAGMENT ENVELOPE

2.75 - INCH FFAR WITH MI5I WARHEAD

NOTE

FRAGMENT TIME IN SECONDS IS GIVEN

ADJACENT TO EACH DATA POINT _

20° IMPACT ANGLE

HORIZONTAL RANGE (FEET)

IMPACT ANGLE

HORIZONTAL RANGE (FEET)

IMPACT ANGLE

Figure 4-1 (Sheet 3 of 3)

Change 1

— —

-4-

"■V

rff

—

■* — ■*-

—

- 1 -

T.O. 1F-4C-34-1-1

ERROR ANALYSIS

DIVE BOMBING

In this mode, the bomb is released from a fixed dive
angle approach to the target. Release is accom¬
plished manually at preplanned airspeed and altitude.
The aircraft flight path is projected beyond the tar¬
get, by means of a depressed sight line, to compen¬
sate for the curvature of the bomb trajectory. See
chart, figure 4-2.

Yp = release altitude (AGL) in feet.

R = bomb range in feet under no-wind conditions.
X parallax factor = 18 feet.

Y parallax factor = 7 feet.

Rq = range correction factor

SIGHT DEPRESSION

Figure 4-2

This chart is drawn to scale for an Ml 17 45° dive,
420 KTAS, 4000 ft. AGL release. The bomb range
for this release condition (obtained from bombing
table) is 3242 ft. Therefore, for this release condi¬
tion, the bomb must be released at a horizontal dis¬
tance of 3242 ft. from the target at the planned 4000
ft. AGL and 45° dive angle. If the 45° dive flight path
is projected from the release point into the ground,
it can be seen that sight depression, sufficient to
project the flight path approximately 760 ft. beyond
the target, is required to compensate for the trajec¬
tory curvature. The formula used to compute de¬
pression settings is as follows:

0 = 17.45[tan -1 Y E -|o|] + a -p

L Rp ± Wpt J

where:

<t> = sight depression in mils.

Y p =Yr - (X parallax factor) sin |o| + (Y
parallax factor) cos |o|

Rp=R - (X parallax factor) cos |o| -(Y
parallax factor) sin |o| + Rq

Wp = release rangewind component in feet/second.

Headwind is minus; tailwind is plus.

t = bomb time of flight in seconds.

0 = release angle in degrees. This is the angle be¬
tween the horizontal and the aircraft flight
path.

a = angle of attack at release in mils.

fi= zero sight line orientation with respect to the
aircraft fuselage reference line in mils.

The quantity

17.45 [tan - 1 Y P -loll
L Rp + Wpt 1 u

in the sight depression angle formula represents the
depression angle from flight path which is listed in
the bombing tables. It is a function of release alti¬
tude, bomb range, and dive angle. Bomb range, in
turn, is a function of release altitude, dive angle,
true airspeed, ejection velocity, and effective drag.
Since many variables are involved and the depression
setting is based on pre-planned conditions, any de¬
viation from pre-planned conditions is bound to result
in impact range error. The following paragraphs in¬
dicate the amount of impact error to be expected for
certain deviations from planned release TAS, alti¬
tude, or dive angle. The following standard or
planned conditions are assumed:

a. Release TAS:

b. Release Alt:

c. Release Angle:

d. Aircraft Gross Weight:

e. Temperature at Release -

Altitude:

f. Wind:

420 kts
4000 ft AGL
-45°

38000 lbs
-18°C

Calm

For these conditions, the sight depression from
flight path is 106 mils and the aircraft angle of at¬
tack at release is 16.66 mils. For simplicity, it will
be assumed that the zero sight line coincides with
the aircraft FRL. This is valid because actual de¬
pression angle from flight path is all that matters.
Using this assumption, the release depression set¬
ting would be 122.66 mils (sum of depression from
flight path and angle of attack). With a fixed depres¬
sion setting assumed, the following equation can be

4-4

T.O. 1F-4C-34-1-1

derived to determine an offset aimpoint required for
a hit if the actual release condition is different from
the planned release conditions.

A = Rp - Yp Cot [o + a A + g P I
*- 17.45 J

| A = Rp-Yp Cot [0 + (<P - a A + « p) (0.0573)J
where:

A = offset aimpoint in feet.

Yp = Ypj - (X parallax factor) sin | 9 | + (Y
parallax factor) cos 191

Rp = R - (X parallax factor) cos 191 - (Y
parallax factor) sin 1 9 | + Rq

Yp = release altitude (AGL) in feet.

R = bomb range in feet.

R^ = range correction factor ( = 0 in sample that
follow)

X parallax factor = 18 feet.

Y parallax factor = 7 feet.

a a = actual angle of attack at release in mils.

0 = release dive angle in degrees.

«p = planned angle of attack at release in mils.

0 = planned depression angle from flight path in
mils.

1 mil = 0.0573 degree.

1 degree = 17.45 mils.

A is an aimpoint offset. If the bomb is released with
the depressed sight on the target, it can be used to
represent impact error. The Yp Cot [ ] part of the
formula provides the horizontal distance from re¬
lease to target for the actual release condition. A
negative A (offset) indicates a negative (short) error,
and a positive A (offset) indicates a positive (long)
error. The offset is zero if all conditions are met.

EFFECT OF RELEASE TAS ERROR

TAS = 400 kts (20 knots slower than planned) 45° dive,
4000 ft AGL, a a = 20.00 mils and R = 3192 feet.
Substituting in the A equation, we have:

A = 3174 - 3992 Cot [ 45° + 106 - 20.00 + 16.66 -,

17.45 J

A = -73 ft (short error)

TAS = 440 kts (20 kts faster than planned) 45° dive,
4000 ft AGL. Using same procedure, a a = 13.81
mils and R = 3288 ft.

A = 3270 - 3992 Cot [45° + 106 - 13.81 + 16.66 ,

17.45 J

A = 65 ft (long error)

EFFECT OF RELEASE ALTITUDE ERROR

Altitude = 3800 ft (200 ft lower than planned) 45° dive,
420 KTAS, a a = 16.66 and R = 3102 ft.

A = 3084 - 3792 Cot [45° + 106 - 16.66 + I 6.66 1

17.45 J

A = 21 ft (long error)

Altitude - 4200 ft (200 ft higher than planned) 45° dive,
420 KTAS, a a = 16-66 and R = 3377.

A = 3359 - 4192 Cot T45° + 106 - 16.66 + 16.661

17.45

A = -27 ft (short error)

EFFECT OF DIVE ANGLE ERROR

Dive Angle = 40° (5° less than planned) 420 KTAS,

4000 ft AGL, a a = 18.05 mils, R = 3749 ft.

A = 3731 - 3994 Cot [40° + 106 - 18.05 + 16.66 1

17.45 J

A = -127 ft (short error)

Dive Angle = 50° (5° steeper than planned) 420 KTAS,
4000 ft AGL, a A = 15.14 mils, R = 2782 ft.

A = 2765 - 3991 Cot [50° + 106 - 15.14 + 16.66 1

17.45

A = 89 ft (long error)

LOW LEVEL BOMBING ERROR
ANALYSIS

In this mode, the bomb is released from a low alti¬
tude level approach at planned airspeed and altitude
above ground. If the depressed sight line is used for
estimating the release point, the procedure used for
the dive bombing error analysis may be used to esti¬
mate low level bomb error resulting from deviation
from planned conditions. Standard conditions as¬
sumed are for release of a BDU-33/B from SUU-
21/A dispenser.

a. Release TAS:

420 kts

b. Release Altitude:

50 ft

c. Release Angle:

0 °

d. Aircraft Gross Weight:

38000 lbs

e. Temperature at

16°C

Release Altitude:

f. Wind:

Calm

For these conditions, the sight depression angle
from flight path is 61 mils, and the angle of attack
is 23.56 mils.

Change 6

4-5

T.O. 1F-4C-34-1-1

EFFECT OF RELEASE TAS ERROR

TAS = 400 kts (20 kts slower than planned) 0’ Release
Angle, 50 ft AGL, a A = 28.29, R = 911.

A = 893 - 57 Cot [0° + 61 - 28.29 + 23.56 ]

17.45

A = -120 ft (short error)

TAS = 440 kts (20 kts faster than planned) 0° Release
Angle, 50 ft AGL, a A = 19.54 mils, R = 1002 ft.

A = 984 - 57 Cot [ 0° + 61 - 19.54 + 23.56 i

17.45

A = 110 ft (long error)

EFFECT OF RELEASE ALTITUDE ERROR

Release Altitude = 40 ft (10 ft lower than planned) 0°
Release Angle, 420 KTAS, a A = 23.56 mils, R =

831 ft.

A = 831 - 47 Cot [0° - 61 - 23.56 + 23.56 i

17.45 1

A = 45 ft (long error)

Release Altitude = 60 ft (10 ft higher than planned) 0°
Release Angle, 420 KTAS, « a = 23.56 mils, R =

1071 ft.

A = 1053 - 67 Cot [0° 4 61 - 23.56 + 23.56 i

17.45 J

A = -42 ft (short error)

EFFECT OF PITCH ANGLE ERROR

Pitch Angle = -1° instead of planned 0 J , 50 ft AGL,

420 KTAS, a A = 23.56 mils, R = 781 ft.

A = 763 - 57 Cot [ 1° + 61 - 23.56 + 23.56 i

17.45

A = 39 ft (long error)

Pitch Angle = +1° instead of planned 0°, 50 ft AGL,

420 KTAS, a a = 23.56 mils, R = 1183 ft.

A = 1165 - 57 Cot [ -1° + 61 - 23.56 + 23.56 i

17.45 1

A = -141 ft (short error)

ROCKET LAUNCHING 2.75-INCH FFAR

As in dive bombing, the depressed pipper is used to
compensate for the curvature of the rocket trajectory
from the launch point to impact. These projectiles
can be delivered more accurately than a bomb under
most circumstances because the high velocity at¬
tained after launch provides a flatter trajectory with
less time of flight. Since the angle of attack is com¬
pensated for in the depressed sight settings, the

following equation is used to compute the offset aim-
point for rocket or gun firing if the actual firing con¬
dition is different from the planned conditions:

A = R p - Yp [Cot 0 4 0 -« ,

17.45 J

where

A = impact error in feet

Rp = R - (X parallax factor) cos | 0| - (Y parallax
factor) sin | 0|

R = horizontal range for actual firing conditions in
feet

Yp = Y - (X parallax factor) sin | 01 4- (Y parallax
factor) cos | 0|

Y = altitude (AGL) in feet at firing
X parallax factor = 18 feet

Y parallax factor = 7 feet

0 = dive angle in degrees at firing

0 = planned sight setting in mils

cia = actual zero sight line angle of attack in mils

A negative A (offset) indicates a negative (short)
error, and a positive A (offset) indicates a positive
(long) error. The offset is zero if ail conditions are
met.

The following paragraphs indicate the amount of
impact error to be expected for certain deviations
from planned firing CAS, altitude, or dive angle.

The following standard or planned conditions are as¬
sumed for launching a 2.75-Inch FFAR with MK-1
warhead:

a. Release CAS: 440 kts

b. Release Alt: 2500 ft AGL

c. Release Ang: -30

d. Aircraft Gross Weight: 40, 000 lbs

e. Target Density Altitude: 5000 ft

f. Wind: Calm

For these conditions the sight setting (0) is 38 mils.
The aircraft angle of attack at release (ctpj is 17.5
mils.

EFFECT OF TAS ERROR

CAS = 420 kts (20 kts slower than planned), 30'dive,
2500 ft AGL, a a = 20.5 mils and R = 4140 ft. Sub¬
stituting in the A equation:

A = 4121 - 2497 Cot [ 30 + 38 - 20.5 i

17.45 1

A = -35 ft (short error)

4-6

Change 3

T.O. 1F-4C-34-1-1

CAS = 460 kts (20 kts faster than planned), 30° dive,
2500 ft AGL, a a = 14.5 mils and R = 4140 ft.

A = 4121 - 2497 Cot [30 + 38 - 14.5 i

17.45 1

A = 22 ft (long error)

EFFECT OF ALTITUDE ERROR

Altitude = 2300 ft (200 ft lower than planned), 30°
dive, 440 KCAS, a a = 17.5 mils and R = 3818 ft.

A = 3799 - 2297 Cot [30 + 38 - 17.5 .

17.45 J

A = 2 ft (long error)

Altitude = 2700 ft (200 ft higher than planned), 30°
dive, 400 KCAS, a a = 17.5 mils and R = 4463 ft.

A = 4444 - 2697 Cot [30 + 38 - 17.5 i

17.45 1

A = -14 ft (short error)

EFFECT OF DIVE ANGLE ERROR

Dive angle = 25° (5° less than planned), 440 KCAS.
2500 ft AGL, a A = I 9 mils and R = 5080 ft -

A = 5061 - 2499 Cot [25 + 38 - 19 i

17.45 1

A = -42 ft (short error)

Dive angle = 35' (5° more than planned), 440 KCAS,
2500 ft AGL, a A = 15.5 mils and R = 3443 ft.

A = 3424 - 2495 Cot [35 + 38 - 15.5 i

17.45

A = 26 ft (long error)

G-LOADING

One of the basic assumptions used in the dive bomb
mission is that the bomb is released from a fixed¬
dive angle approach. Any increase in G-loading dur¬
ing the approach results in an increase in aircraft
angle of attack. This decreases effective sight de¬
pression relative to the flight path and produces an

ANGLE OF ATTACK vs G-LOADING

DECREASE IN ANGLE INCREASE IN ANGLE

OF ATTACK - MILS OF ATTACK - MILS

F4 34-IV-102

Figure 4-3

undershoot (or short impact) situation. The converse
is true for a decrease in G-loading.

Normally, G-loading errors will result from an im¬
proper roll-in and the resulting improper initial
tracking index position in relation to the target. If
the initial tracking index position is too close to the
target, the pipper will, during the dive, move up to
the target prior to the pre-planned release altitude.

In this case, a push-over (bunt maneuver) would be
required to keep the tracking index from moving past
the target. This would decrease angle of attack, in¬
crease dive angle and effective sight depression an¬
gle, and result in an overshoot. The validity of the
sight depression setting computation is destroyed if
a bunt maneuver is initiated, since the whole theory
of the computation is based on a fixed dive angle ap¬
proach. Figure 4-3 illustrates the effect of G-loading
on angle of attack.

Change 3

4-6A/(4-6B blank)

T.O. 1F-4C-34-1-1

SIDESLIP ANGIE/BALL DEFLECTION

SIDESLIP (YAW) ANGLE - DEGREES

F4-34-IV-103

UNCOORDINATED FLIGHT

At release, the weapon follows the aircraft flight
path direction with respect to the earth. Conse¬
quently, if the aircraft approaches the target in a
skid, and releases the weapon with the tracking index
on the target, the weapon will impact in the direction
of the skid (along the flight path). Uncoordinated
flight is reflected on the turn and bank indicator by
a displacement of the ball. The following chart,
figure 4-4 based on flight test data, provides data
on side slip angle (degrees per ball-width) vs KCAS.

Enter the chart with release indicated airspeed, pro¬
ceed horizontally until the curve is intersected, and
project downward to the margin. The figure indicates
the degrees of side slip angle per ball width at a
given CAS, i.e., at 350 knots, one ball width deflec¬
tion equals 1° of yaw.

The approximate error resulting from release in a
skid would be the skid angle (in mils) times the re¬
lease slant range divided by 1000. Thus, if the pilot
releases at a 5000 ft range, in a 20 mil skid, the im¬
pact error should be 100 ft in the direction of the
skid.

Figure 4-4

HARMONIZATION OF AIRCRAFT GUNS

The term "harmonization” refers to the procedure
used to orient the optical sight tracking index, the
radar, and gun armament with the F-4 aircraft. More
specifically, the procedure involves the alignment of
this equipment so that - when airborne - the tracking
index (pipper) indicates the point of projectile impact.
Harmonization methods for F-4D/E aircraft can be
more involved than for F-4C aircraft. This is pri¬
marily due to the differences in reticle alignment
procedures for the lead computing optical system
(F-4D/E) and the fixed optical system of the F-4C.
The optical alignment procedure for the F-4D/E can
involve the complete removal of the sight. For the
F-4C, alignment is accomplished in the cockpit. (See
T.O. 1F-4C-2-18). With reticle alignment procedures
complete, however, gun harmonization methods for
any F-4 gun system are nearly the same.

Theoretically, all gun projectiles should follow the
same flight path or trajectory and should strike a
common point. However, certain factors cause dif¬
ferent projectile trajectories, thus causing impacts
in a defined area, rather than at a common point.

This phenomenon is known as dispersion. Dispersion
is caused by variations in manufacturing tolerances,

barrel whip, changes in the statics and dynamics as
the gun accelerates and decelerates, slight rate
variations during steady-state firing, and variations
in ammunition characteristics.

Harmonization of the aircraft is attained by orienting
the guns to the optical sight through the use of har¬
monization targets. Basically, it is the alignment of
three reference lines: the fuselage reference line,
the sight line, and the timed barrel line. Two meth¬
ods of harmonizing the F-4 aircraft are defined as
the Boresight method and the Ground Fire method.

BORESIGHT METHOD

The boresight method is performed at either a 1000-
inch or a 1000-foot range using a target designed
specifically for these ranges. First, the aircraft is
aligned with the target using a datum fixture and tele¬
scope assembly which is mounted to the nose gear
well structui’e. Next, the optical sight is aligned to
the target board using the sight pipper (F-4C) or an
alignment telescope assembly (F-4D/E). (The lead
computing sight unit is removed if the pipper is
misaligned more than 50% in azimuth from a circle

4-7

on the target board. Then the sight mounting platform
is aligned using a telescope assembly, and the sight
unit is bench aligned. If pipper misalignment is less
than 50%, the necessary adjustments may be accom¬
plished in the cockpit.) The guns are then aligned to
the target gun boresight point by using an offset
boresight adapter and telescope assembly. The bore-
sight adapter is mounted directly on the gun barrels,
and the alignment is physically accomplished by gun
azimuth and elevation adjustments.

Considering the gun pods, the boresight adapter is
mounted to the barrels at the mid barrel clamp; the
telescope is positioned out to the side of gun pod cen¬
terline. This arrangement is particularly advanta¬
geous for the CL pod since it precludes the necessity
of having to raise the nose gear in order to sight the
target. During the process of boresighting the CL
gun pod on the 1000-inch target, an auxiliary bore¬
sight point may be located and marked on the nose
gear door. This point may be used for a future quick,
check of CL pod alignment without using a target.

Considering the F-4E nose gun, the mechanics of
boresighting are basically the same as stated above.
The difference is that the boresight adapter tool
mounts directly into the firing barrel in the timed
position. During the boresight alignment process on
the target board, an auxiliary (back boresight) point
may be located and marked on the aft fuselage section
for future quick check purposes. The telescope as¬
sembly may be reversed in order to sight on the back
boresight point.

Note

After nose gun firing operations, it has been
observed that the gun vertical adjustment
mechanism may become loose. Hence, load
crews must check the mechanism tight during
each gun loading operation. The mechanism
may be tightened with no requirement for ad¬
ditional harmonization procedure.

GROUND FIRE METHOD

The ground fire method of harmonization can be ac -
complished on a 1000-inch range or ranges varying
in length from 500 to 2250 feet. When this method is
used, an aircraft tie-down pad and a firing-in butt
are required. Prior to firing the guns, the aircraft
must be jacked and established at a +2.0° attitude.
Next, the optical sight and guns must be boresighted
and the aircraft tied down. The nose landing gear
must be raised for CL gun pod firing operations.

The guns can then be fired and adjusted.

The ground fire procedure permits the guns to settle
in their mounts, and to some extent, permits further
control over factors affecting shot dispersion. The
net result is more complete control over small errors
that will be magnified in an actual firing situation.

The method also checks gun operation and inspires
crew confidence in the gun systems.

The harmonization procedure should be accomplished
after uploading the pods, after a major aircraft in¬
spection, after a barrel change or major gun compo¬
nent change, and after the sight unit has been re¬
moved. The AC will notice the need for harmonization
when projectile impact is in obvious error. Also, the
procedure should be conducted every 15 to 20 mis¬
sions, or once a week during extensive gunnery op¬
erations.

PARALLEL vs. CONVERGED FIRE

CONVERGED FIRE

PARALLEL FIR.

F4-34-IV-104

Figure 4-5

CONVERGED VS. PARALLEL FIRE

With the multiple gun firing stations available, pos¬
sible methods of harmonization include either the
convergent or the parallel methods (figure 4-5). For
F-4 aircraft, the convergent method is used to pro¬
vide the maximum consistent projectile density of
the rounds fired. The specified density for accept¬
able harmonization of the gun pods is eighty percent
of the rounds fired impacting in an 8-mil cone (18
feet at 2250 feet). The cones of dispersion for the
gun pods are illustrated in section I, part 4 of this
manual. The specified density for the nose gun is
eighty percent of rounds fired in a 10 mil cone (22.5
feet at 2250 feet).

PARALLAX ERROR

The term parallax, where the deployment of aircraft
weapons is involved, may be defined as the displace¬
ment or separation between the optical sight reticle
and the point at which the specific armament is sus¬
pended (the timed barrel in the case of guns). A
parallax sighting error results from this separation,
and any correction applied must be accomplished in
terms of the vertical parallax component and the
horizontal component. The average vertical parallax
component is 7.0 feet; the average horizontal compo¬
nent is 18.0 feet. These dimensions must be consid¬
ered whenever sight depression charts are developed
for the air-to-ground deployment of any armament
using the optical sight as an aiming reference. The
correction, which is applied in terms of mils, is in¬
cluded in sight depression charts in this manual.

T.O. 1F-4C-34-1-1

WRCS OPERATIONAL ENVELOPE (DIVE TOSS MODE)

Operational envelopes that show WRCS Dive Toss
delivery limitations are shown in figures 4-6 and
4-7. Figure 4-6 considers the computer system
before T.O. 1F-4-702. Figure 4-7 dimensions con¬
sider the computer after T.O. 1F-4-702, which re¬
moves several operational restrictions imposed by
the figure 4-6 computer. Figure 4-7 is therefore
considered self-explanatory and the following dis¬
cussion largely applies to the computer system of
figure 4-6.

COMPUTER ACCURACY

In figure 4-6, two envelopes are shown to illustrate
the boundary limits that determine the guaranteed
computer accuracy; one for ± 150-foot computer
accuracy, the other for ± 300-foot computer accu¬
racy. The ± 150-foot accuracy envelope is bordered
by 10-degree and 45° dive angles and 10,000 feet
maximum slant range at pickle. The ± 3000-foot
accuracy envelope is bordered by 10° and 60° dive
angles and 20,000 feet maximum slant range at
pickle (excluding the ± 150-foot accuracy envelope).

MAXIMUM RELEASE ALTITUDE

The 5000-foot maximum release altitude (above tar¬
get) limitation resulted out of a modification to pre¬
vent an inadvertent bomb release when the pickle
signal occurred at slant ranges greater than 20,000
feet. If the aircraft is not below the 5000-foot maxi¬
mum release altitude when bomb release occurs; (1)
bomb impact will be long of the target since the com¬
puter will establish the release point based on a re¬
lease altitude of 5000 feet above tax-get regardless of
the actual release altitude, or (2) the bomb release
solution may not occur and the bomb will not be re¬
leased. This restriction is removed by T.O. 1F-
4-702 (figure 4-7).

MAXIMUM PULL-OUT ALTITUDE
(PICKLE ALT)

The maximum pullout altitude limitation curves (fig¬
ure 4-6) show the conditions at the time of pickle

(bomb release button depressed) that will place the
aircraft less than 5000 feet above target at the time
when automatic bomb release occurs, assuming that
the pullout maneuver is initiated immediately after
pickle. The curves are typical for the MK 83 or
Ml 17 GP bomb, an airspeed of 480 KTAS at the time
of pickle, and assume that the selected G accelera¬
tion is obtained 2 seconds after pickle. The curves
would be lower in altitude if an airspeed lower than
480 KTAS is used or if the G acceleration rate is
increased. This is true because the altitude lost dur¬
ing pullout would be less and the bomb release angle
would be greater. If the bomb is released above 5000
feet, the computer solves the ballistic equation based
upon a 5000-foot release altitude and the impact will
assume the corresponding altitude error. Refer to
maximum release altitude above target curve de¬
scription.

MINIMUM PULL-OUT ALTITUDE

The minimum pullout altitude curves (figures 4-6 and
4-7) are established for fuze/arming requirements,
fragmentation avoidance, aha terrain avoidance. The
fragmentation and fuze arming curves assume bomb
button depressed at the time of pullout initiation. All
curves are based on 480 knots TAS and 4.0-G pullout
acceleration. Aircraft ground clearance is assumed
to be 500 feet for dive angles of 30° and below, and
1000 feet for dive angles of 35° and above.

10-DEGREE CLIMB ANGLE

The accuracy of the computer is not guaranteed when
bomb release occurs at aircraft climb angles greater
than 10°. The curve (figures 4-6 and 4-7) illustrates
that for the range of the MK 82 and Ml 17 GP bomb,
the altitude/range conditions of the aircraft at pickle
must be above the curve to obtain a bomb release
prior to reaching a 10° climb release angle. The
curve assumes a 4.0-G pullout initiated immediately
after pickle. The cux-ve would be lower in altitude
and greater in range for a lower pullout acceleration.

4-9

T.O. 1F-4C-34-1-1

DIVE TOSS OPERATIONAL ENVEL OPE F-4D

PRIOR TO T.O. 1F-4-7Q2

• AN ASQ-91 Mod 3 Weopon Release Computer System.

• BOMB: MK 83 LDGP or Ml 17 GP

• Airspeed at Pickle: 480 KTAS

• Minimum Recovery Altitude: 30° and below - 500 ft; 35° and Above ~ 1000 ft.

• Minimum 4.0G Pullout Altitude (Pickle Alt) for:

a. MK 83 LDGP Bomb Fuze Arming, M904 Fuze with 4-sec Arm Delay Selected.

b. MK83 LDGP Bomb Fragment Clearance.

Notes

Pullout altitude is the altitude where the pullout
maneuver is initiated. Pickle altitude is the al¬
titude where the bomb release button is depressed
and the pullout maneuver is initiated.

HORIZONTAL DISTANCF TO TARGET - 1000 FEET

t—

HORIZONTAL DISTANCE TO TARGET - 1000 FEET

F4-34 -IV-105

Figure 4-6

4-10

Change 1

ALTITUDE ABOVE TARGET - 1000 FEET

T.O. 1F-4C-34-1-1

VIVE TOSS OPERATIONAL ENVELOPE

F-4D AFTER T.O. 1F-4-702 AND ALL F-4E

HORIZONTAL RANGE TO TARGET - 1000 FEET

18.000 FOOT ALTITUDE LIMIT

+ 350 FEET
COMPUTER
ACCURACY

11111 1320 FEET M
m ■■ - COMPUTER m

ACCURACY

±160 FEET
COMPUTER
ACCURACY

GROUNO
CLEARANCE
LIMIT (4.0 G
PULLUP)

10 DEGREE CLIMBLIMIT
(4.0 G PULLOUT)

HORIZONTAL RANGE TO TARGET - 1000 FEET

OUTER LIMITS ARE BASE ON COMPUTER OPTIMUM OPERATIONAL
CAPABILITIES WITH INCORPORATION OF T.O. 1F-4-702.

ACCURACY BOUNDRIES DEFINE EXPECTED COMPUTER ACCURACY
ASSUMING OTHER INPUT SYSTEMS PERFORM AS SPECIFIED.

ALL BOUNDRIES ARE BASED ON AIRCRAFT POSITION AT TIME OF PICKLE.

FUZING AND GROUND CLEARANCE LIMITS BASED ON 4.0G PULLUP ATTAINED
IN 2.0 SECONDS, 480 KNOTS TAS.

M-904 NOSE FUZE ASSUMED FOR MK-83 BOMB.

Figure 4-7

Change 1

4-11

ALTITUDE ABOVE TARGET - 1000 FEET

T.O. 1F-4C-34-1-1

CTO-1/A RESUPPiy CONTAINER

THE ALLOWABLE CENTER OF
GRAVITY RANGE INCLUDES ALL
SITIONS FORWARD OF THE AFT LIMIT

STA.,20

DISTANCE FROM STATION 20 TO AFT LIMIT C.G.-INCHES

F4-34-1 V-l11

Figure 4-8

CTU-1/A RELEASE STABILITY

ALLOWABLE CG RANGE

The chart in figure 4-8 is provided to establish a
limit CTU-l/A CG in order to verify container sta¬
bility at release. The chart locates the most aft
allowable CG position as a function of container pay-
load weight and release calibrated airspeed. The
measurement is expressed as the distance between
the leading edge of the center section (station 20) and
the most aft center of gravity (figure 4-8). The
allowable CG therefore includes any point forward of
the aft limit. Enter the chart with the planned pay-
load weight, project to the planned release calibrated

airspeed, and down to read the aft limit. The actual
CG must be forward of this point.

CAUTION}

If the actual CG is aft of the chart measure¬
ment, then the release speed and/or payload
weight must be adjusted to establish an ac¬
ceptable CG position. Failure to observe the
required CG limits can result in unstable
separation characteristics.

4-12

UNCLASSIFIED

SECTION V

PLANNING PROCEDURES and
SAMPLE PROBLEMS

T.O. 1F-4C-34-1-1

TABLE OF CONTENTS

REFERENCE LINES

5-18

5-22

5-26

The purpose of this section is to provide the aircrew
with the data required to plan a weapon delivery mis¬
sion with the non-nuclear bombs and rockets, and
the practice bombs used with the SUU-20/A or SUU-
21/A dispenser, and illustrate the planning procedure

procedures considerably, depending on the delivery
mode selected; however, safe escape from fragmen¬
tation and ground clearance is always the responsi¬
bility of the aircrew. When the DIRECT delivery
mode is selected, mission planning procedures for
the F-4D/E aircraft are the same as for the F-4C
aircraft. The last page of the Mission Planning Form
(figure 6-1) outlines the WRCS parameter for the
various delivery modes.

REFERENCE LINES

The various reference lines used in this manual are
illustrated in figure 5-1. Other possible identifica¬
tions of a particular reference line are also stated.

The ballistic tables in T.O. 1F-4C-34-1-2 are based
on the ICAO standard day conditions with the target
at sea level. Ambient pressure and temperature
variations from the standard day are considered to
have negligible effect on trajectory accuracy. This
assumption is valid for most non-nuclear weapon de¬
livery conditions because the weapon time of flight is
generally small. The loft ballistic tables are based
on density altitude.

The Weapons Release Computer Set (WRCS) in the
F-4D/E aircraft has reduced the mission planning

A. FRL (Fuselage Reference Line/
Armament datum line or water line)

B. MAU-12 Armament pylon line.

C. Radar boresight line.

D. Aircraft flight path.

E. Depressed pipper sight line.

1. ANGLE OF ATTACK FROM ZERO SIGHT LINE.

2. ANGLE: TWO DEGREES (35 MILS) BELOW FRL.

3. MAU-12 PERMANENTLY RIGGED ONE DEGREE BELOW FRL.

4. SIGHT DEPRESSION FROM FLIGHT PATH.

Figure 5-1

Introduction. 5-1

Description of Charts and Tables. 5-3

Dive Bombing and Low Level Bombing
Sample Problem. 5-11

Rocket Launch and Gun Firing Sample

Problem.

Loft Bombing Sample Problem . . .
Inflight Considerations.

INTRODUCTION

T.O. 1F-4C-34-1-1

PRESSURE ALTITUDE

Pressure altitude is the altitude measured from
standard sea level pressure, 29.92 inches of mer¬
cury (Hg). Pressure altitude is also the altitude read
on the altimeter when set on 29.92 in. Hg. Target
pressure altitude, used in mission planning, is
obtained from the weather forecaster or based on the
prevailing pressure altitude.

Target pressure altitude can be computed if the altim¬
eter settings for the target area is known. Subtract
29.92 from the altimeter setting and apply the stand¬
ard lapse rate (0.10 in. Hg. = 100 feet) to the pres¬
sure difference. If the altimeter setting is higher
than 29.92, subtract the altitude difference from tar¬
get elevation (MSL). If the reported altimeter set¬
ting is lower than 29.92, add the altitude difference to
the target elevation (MSL).

Example: Altimeter setting (-H, +L) -30.62 in. Hg
Standard datum plane: 29.92 in. H g

Pressure difference: - 0.70 in. Hg

Lapse Rate (100 ft/0.10 in.) = -700 ft.

Release altitude (MSL): 4000 feet

Altitude difference: -700 feet

Release pressure altitude: 3300 feet

Note

If release pressure altitude is not known, re¬
lease altitude MSL may be used (i.e. release
altitude AGL, plus target elevation MSL).

D VALUE

The D (difference) value is the difference between
true altitude and pressure altitude. The weather
forecaster will provide the current D value for the
requested altitude. The D value changes with alti¬
tude since ambient conditions seldom correspond to
the standard lapse rate. The D value should be used
to establish the indicated approach altitude and to
establish the altitude set into the WRCS ALT RANGE
control for the offset bomb and target find modes.

USING THE D VALUE
Mission Conditions

a. Approach Altitude AGL 1000 ft

b. Target Elevation MSL 2000 ft

c. Target Surface Altimeter Setting 30.02

d. Approach Altitude D Value +250 ft

ALT RANGE CONTROL SETTING

a. Target Elevation MSL 2000 ft

b. Approach Altitude D Value -250 ft

(Reverse Sign)

c. ALT RANGE Control Setting 1750 ft

Note

When the D Value is not available, set the
ALT RANGE control with the IP or target
pressure altitude. When there is a signifi¬
cant difference between the radar IP and tar¬
get elevation, also establish the ALT RANGE
setting for the radar IP.

Indicated Altitude When Flying 29.92

a. Approach Altitude MSL 3000 ft

b. Approach Altitude D Value -250 ft

(Reverse Sign)

c. Indicated Approach Altitude 2750 ft

Indicated Altitude When Flying Surface Altimeter

a. Surface Altimeter Setting (-Il,+L) -30.02

b. Standard Datum Plane 29.92

c. Pressure Difference inches Hg -0.10

d. Multiply by x 1000

e. Pressure difference in feet -100 ft

f. Approach Altitude MSL 3000 ft

g. Approach Altitude D Value -250 ft

(Reverse Sign)

h. Pressure difference in feet +100 ft

(Reverse Sign)

i. Indicated Approach Altitude 2850 ft

IMPACT PATTERN FOR
RIPPLE RELEASE

The length of the impact pattern for a ripple release
can be determined from the following formula:

P.L. = [ (I R ) (1.69) (V R ) (Cos 0) (N-l)] - A R

P.L. = Pattern length in feet.

Ir = Release interval in sec.

Vr = Release TAS in knots.

0 = Release dive angle in degrees

N-l = Number of bombs in ripple, minus
one bomb.

A R = Difference in feet between range of
first and last bombs released during
the ripple sequence.

1.69 = The constant used to convert knots to

feet per second. (If Vr is in fps, 1.69
must not be included in the formula.)

Note

A R is zero for level releases at constant
TAS. For dive releases, interpolation in the
tables will be required to determine A R.

The release altitude for the last bomb in the
ripple will be (Ir) (1.69) (V^) (Sin 0)(N-1)
feet lower than the first bomb release alti¬
tude.

5-2

T.O. 1F-4C-34-1-1

For example, assume a six-bomb M117 ripple re¬
lease, at 0.14-second intervals, released at 480
knots TAS, in a 30° dive, from 2500 feet AGL. Using
(I R ) (1.69) (V R ) (Sin A) (N-l), the last bomb in the
ripple will be 284 feet lower than the first bomb.
Therefore, the release altitude of the last bomb will
be 2216 feet AGL. Select the proper bombing table
(T.O. 1F-4C-34-1-2) for the planned 30° dive, 2500
feet AGL, 480 knots TAS release condition and ob¬
tain the range of the first bomb in the ripple, 3538
feet. Using the same table, interpolate at the re¬
lease altitude of the last bomb, 2216 feet, to obtain
the range of the last bomb in the ripple, 3186 feet.
The difference in feet between these two ranges will
provide the A R in the pattern length computation,
352 feet.

A R = 3538 feet - 3186 ft. = 352 ft.

P.L. = 0.14 (480 kts 1.68) Cos 30 (6-1)

-352 ft.

P.L. = 140 feet

SIGHT SETTING COMPUTATION

attack, plus sight depression angle from flight path,
equals the optical sight setting for zero wind.

Wind correction can be applied to the sight setting or
wind correction can be made by estimating an upwind
aimpoint. The tables provide the data required for
both methods of wind correction. The mil correction
is added for headwind and subtracted for tailwind.

INTERPOLATION OF BALLISTIC
TABLES

When it is deemed necessary to interpolate the bal¬
listic tables, the following review may be helpful.
Assume that the sight depression is to be interpo¬
lated for 420 knots TAS:

400 knots = 15.4 mils
450 knots = 13.7 mils
1.7 mils

(450 knots) - (420 knots) . 7
(450 knots) - (400 knots)

x 1.7 = 01.02 mil

The bombing tables provide the sight depression 1.02 + 13.7 = 14.72 mils

angle from flight path. Use the angle of attack chart

to find the aircraft angle of attack in mils. Angle of 420 knots = 14.7 mils

DESCRIPTION OF CHARTS AND TABLES

MISSION PLANNING FORM

The mission planning form (figure 6-1) provides a
convenient sequence for planning a non-nuclear
weapon delivery mission. The planning form is
divided into seven parts. The first three parts (Mis¬
sion Conditions, Release Conditions, and Wind
Values) are applicable to all delivery modes. The
remaining four parts (Dive and Low-Level Bombing
Conditions, Rocket Launch and Gun Firing Con¬
ditions, Loft Bombing Ripple Release Conditions and
WRCS Counter Settings) are applicable only to de¬
livery mode implied.

DIVE RECOVERY CHARTS

The dive recovery charts (figure 6-2) are used to
determine the altitude lost during pullout after bomb
release. The charts are based on an acceleration of
3.0 G, 4.0 G, or 5.0 G obtained in 2 seconds after
release. For conditions when C^ max is reached,
the curves follow the buffet boundry. Enter the
chai't with release velocity TAS, project to the dive
angle and across, to read altitude lost. Release
altitude must be greater than the sum of altitude lost
during pullout and minimum recovery altitude. This
chart contains no reaction time and no safety factors.

Figure 6-2, sheet 4 presents the altitude lost during
recovery when performing a 4.0 G pullup in a banked

turn. The altitude lost for the following conditions is
provided:

a. Dive angle: 15°, 30°, and 45°.

b. True airspeed when pullup is initiated.

c. Bank angle during the pullup: 0° (wings level
pullup), 10°, 20°, 30°, and 45° turns.

Note

The pullup acceleration is assumed to be
4.0 G obtained in 2 seconds.

ANGLE OF ATTACK CHART

The angle of attack chart (figure 6-3) is used to de¬
termine the aircraft fuselage angle of attack. The
purpose of the chart is to aid in computing the optical
sight depression angle in mils. The unit of measure¬
ment used to calibrate the mil scale is: 1° = 17.45
mils, or 1 mil = 0.0573°. The zero sight setting (or
sight line) is at the fuselage reference line. Enter
the chart with the release calibrated airspeed, pro¬
ject to the aircraft gross weight at release, project
to the preplanned dive angle, project right, and read
the fuselage angle of attack in mils. To determine
the optical sight setting, add the angle of attack to the
sight depression from flight path obtained from the
sight depression charts (figure 6-10) or the bombing
tables.

5-3

T.O. 1F-4C-34-1-1

Note

F-4D/E Aircraft. When the optical sight is
pitch stabilized, angle of attack is not added
to the sight depression from flight path. The
sight is pitch stabilized in all LABS modes
and in the WRCS LAYDOWN mode. When the
optical sight is pitch stabilized, the maximum
usable sight setting is a function of angle of
attack and transit changes in pitch attitude.

For example, with an angle of attack of 60
mils, the max setting is (245-60) 185 mils
minus anticipated changes in pitch attitude.

Also, during the pullup portion in a loft ma¬
neuver, the sight reticle will not be visible
above 20".

AIRSPEED CONVERSION CHART

The airspeed conversion chart (figure 6-4) presents
the relationship of calibrated airspeed (CAS), true
airspeed (TAS), and true Mach number as a function
of free-air temperature (outside air temperature) in
degrees centigrade, and true pressure altitude. If
true pressure altitude at release altitude (or at ap¬
proach altitude for loft bombing) is not available, the
release altitude above mean sea level (MSL) may be
used.

Note

For the F-4E. indicated airspeed and cali¬
brated airspeed are considered to be equal;
position error correction is not required.

ALTITUDE CONVERSION CHART

The altitude conversion chart (figure 6-5) is used to
determine the density altitude for a given pressure
altitude (or altimeter setting) and temperature. The
loft ballistic tables, the rocket launch and gun firing
tables in T.O. 1F-4C-34-1-2 are presented as a
function of density altitude.

SIDE EJECTION IMPACT DISTANCE

The side ejection charts (figure 6-6) empirically
show the expected impact dispersion due to MER/
TER lateral ejection forces applied at release. The
plots are based on the following factors;

a. An ejection velocity as a function of store weight.

b. A MER/TER ejection vector of 45" to the side.

c. Outboard MER canted 7.5° from vertical.

d. The distance of the inboard and outboard stations
from the airplane centerline.

The error distance is shown with respect to the cen¬
terline of the aircraft and as a function of time from
release to impact.

ALTIMETER POSITION ERROR

The table in figure 6-7 shows the expected altimeter
position error for level flight weapon delivery con¬
ditions; The table is applicable to F-4C-24 thru 29
and F-4D-24 thru 29 after T.O. 1F-4-754. After

T.O. 1F-4-754 (and all F-4E aircraft), the error
becomes zero plus or minus whatever error is noted
during preflight operations. The table is used in mis¬
sion planning to establish the indicated weapon re¬
lease altitude with static correction operating. Ad¬
ditional information is available in T.O. 1F-4C-1.

ALTIMETER LAG CHART

During a dive, the altimeter does not unwind at a
rate equal to the actual rate of aircraft descent. The
altimeter lag chart (figure 6-8) provides the altitude
that should be added to obtain an indicated release
altitude above ground level. Enter the chart with re¬
lease velocity TAS, project to the dive angle, and
down to read altimeter lag.

SINE AND COSINE TABLE

The sine and cosine table (figure 6-9) is used to com¬
pute the bomb impact pattern length for a ripple re¬
lease, and to compute the release altitude of the last
bomb.

SIGHT DEPRESSION CHART

The sight depression charts (figure 6-10) provide the
sight angle in mils for a given release altitude AGL
and horizontal distance from release to impact for
dive angles from level flight, 5" dive thru 60° dive.
Enter the chart with distance, project to the release
altitude above target, and read the sight depression
angle from flight path in mils. To compute the final
sight setting, algebraically add the angle of attack
from zero sight line and wind correction factors.
Parallax correction factors are included in these
charts. Parallax correction is necessary to compen¬
sate for the vertical and horizontal distance between
the sight head and the bomb rack.

RELATIVE WIND VECTOR CHART

When forecast wind data are used for mission plan¬
ning, the relative wind vector chart (figure 6-11) is
used to obtain the rangewmd and crosswind compo¬
nents. The wind velocity at release altitude should
be used. The displacement of the bomb is a function
of initial velocity and time of flight. As the time be¬
comes less, the magnitude of deflection is also less.
Use the relative wind vector chart as follows:

Given; a. Forecast wind velocity: 350°/30 knots,
b. Approach course to target: 040°.

Find; a. Relative wind direction: 310".

b. Rangewind component: 20 knots headwind.

c. Crosswind component: 23 knots left.

Relative wind direction must be determined before
entering the relative wind vector chart. Obtain
relative wind direction by subtracting approach
course to target, 040°, from forecast wing direction
over target.

350" - 040° = 310" relative wind direction.

5-4

520

RELATIVE WIND VECTOR

Figure 5-2

Note

If the aircraft course to target is greater
than the wind direction, add 360° to the wind
direction; then subtract aircraft course from
the wind direction to obtain relative wind
direction.

Enter the sample relative wind vector chart (figure
5-2) with 310°. Project to the 30-knot wind circle
and over to the horizontal and the vertical axes:
read the rangewind and crosswind components re¬
spectively.

WIND CORRECTION

OFFSET AIMPOINT

For level delivery of the high drag bombs (Snakeye I,
CBU's), crosswind correction is usually achieved by
crabbing the aircraft into the wind and offsetting the
ground track in the upwind direction parallel to the
no-wind course. Rangewind correction is accom¬
plished by correcting the sight setting by releasing
early or late. The equation for rangewind correction
is as follows:

(Rangewind in knots) (t c ) (1.69) = correction in feet.

When the aircraft is crabbed to maintain a ground
track during the approach and release, the need for
crosswind correction is reduced, as illustrated by
the following equation which is valid for both high
drag and low drag bombs.

T.O. 1F-4C-34-1-1

(Crosswind in knots|^(t c ) (1.69) -

When the aircraft is drifting (not crabbed), the
rangewind and crosswind correction factors are the
same:

(Wind in knots) (t c ) (1.69) = correction in feet
where:

tc = Bomb time of fall in seconds.

Rg = Bomb range in feet.

V A = Release velocity in knots TAS

1.69 = Conversion factor to change knots to feet
per second.

For the low-altitude level delivery of the low drag
bombs, crosswind correction is usually achieved by
crabbing the airplane into the wind so that the air¬
craft ground track will pass through the target. The
equation will show that an offset ground track is not
required.

When the crabbing technique is used with a sight that
is not drift stabilized, the pipper will not be directly
on the target when release occurs; because of the
crab angle, there will be an apparent increase in the
sight angle. As the crab angle increases, the pipper
scribes an imaginary arc through the target radiating
from the release point. Therefore, the bomb should
be released when the pipper is on the arc which will
appear to be short of the target.

UP WIND AIMPOINT

The up-wind aimpoint method of wind correction can
be used for all delivery modes and all non-nuclear
weapons. The total wind speed at release altitude is
used to relocate the aimpoint up-wind from the tar¬
get by an amount equal to the product of the total
wind speed times the weapon time of fall. The up¬
wind aimpoint may be approached from any direction,
The no-wind sight setting is used and the weapon is
released at the planned release conditions. The air¬
craft is drifting, i.e., no attempt is made to correct
the aircraft for drift by crabbing.

WIND CORRECTION - WRCS MODES (F-4D/E)

No corrections for the effects of wind should be re¬
quired for the delivery of low drag bombs with the
F-4D/E aircraft using the dive toss bombing mode.
When using the dive laydown, laydown, or offset
bombing mode, the low drag bomb should be released
at a ground speed that is equal to the planned true
airspeed range of the bomb and the aircraft should be
crabbed to maintain a ground track through the target.

When high drag and medium drag bombs are released
from altitudes of 100 feet or less with wind conditions
less than 10 knots, wind effects produce errors of
less than 50 feet. Higher altitudes or higher wind
conditions can be tolerated (without wind corrections)
when the ripple release mode is used to minimize
range error; the flight path is offset in the upwind

Change 7

5-5

T.O. 1F-4C-34-1-1

direction. The equations for wind correction when
the bomb is released at the planned true airspeed is:

(Rangewind in knots) (t c ) (1.69) = correction

in feet.

(Crosswind in knots) (t c ) (1.69 - R 3 ) = correction

in feet.

DIVE ANGLE VS DISTANCE CHART

The dive angle vs distance chart (figure 6-12) pro¬
vides a means to approximate the distance from tar¬
get for a given dive angle and altitude and determine
the slant range. Trajectory drop can also be com¬
puted. To determine the trajectory drop, place a
mark on the chart at the intersection of release alti¬
tude and dive angle: project down and find distance.
Subtract the bomb range from the distance to obtain
the trajectory drop. This chart is provided as sup¬
plementary data and is not used in the sample prob¬
lem.

FUZE ARMING AND SAFE ESCAPE

WARNING

• The lower release conditions provided in the
ballistics tables in T.O. 1F-4C-34-1-2 must
be checked with the Fuze Arming and Safe
Escape tables (figures 6-13 thru 6-16) and
the Dive Recovery charts (figure 6-2) in
section VI of this manual to ensure a safe
delivery condition.

• Refer to section I, part 4, for fuze descrip¬
tion, operating restrictions, and arming
tolerance. Refer to T.O. 1F-4C-1 for Ex¬
ternal Stores Limitations.

FUZE ARMING

Fuze arming is the vertical distance below the air¬
craft where the fuze will be unarmed. If bomb impact
occurs within the fuze arming distance, a dud bomb
is predicted. _

WARNING

•When the MK 82 Snakeye I or Ml 17 retarded
bombs are configured for in-flight selection
of high/low drag release, the minimum
M904E2/E3 nose fuze setting is 6.0 seconds
and the low drag bomb time flight must be
greater than 6.6 seconds.

•Ila 2 -second nose fuze arming time is used
and the bomb is release low-drag, the air¬
craft will be within the lethal fragment en¬
velope when the fuze is armed.

Note

If the retarded bombs are configured to ex¬
clude cockpit selection of low drag delivery,
a 2 -second nose fuze arming delay setting
may be used.

For the M904 and M905 fuzes, only the 4 and 6-sec¬
ond arming delay settings are considered for low
drag bomb releases. Current tolerances listed for
the arming delay times are ±10 percent of the delay
settings. The delay setting plus the positive toler¬
ance was used in the determination of minimum re¬
lease altitude, or vertical drop required for these
fuzes to arm. For example, the 4-second arming
delay setting will require a minimum bomb time of
fall of 4.4 seconds. The 6-second arming delay set¬
ting requires a minimum time of fall of 6.6 seconds.

SAFE ESCAPE

Dive Delivery

Safe escape is the vertical distance above the ground
that includes the fragment envelope. Safe escape is
also the vertical distance above the ground where
the pilot must initiate pullout to ensure a minimum
ground clearance. Normally, the minimum ground
clearance for dive angles of 30° and less is 500 feet;
for dive angles of 35° and greater is 1000 feet. The
minimum release altitude for aircraft ground clear¬
ance is based on a 4.0-G pullout and assumes that
4.0 G is obtained in 2 seconds after the last bomb
release.

Level Delivery

The minimum release altitudes for the level release
of retarded and freefall (unretarded) GP bombs are
provided in the safe escape tables. Two escape ma¬
neuvers are provided: (1) 4.0-G MIL power pullout
at release and ( 2 ) straight and level, constant speed
recovery. The level release followed by a 4.0-G MIL
power pullout is safe only for single bomb release.
The G is maintained until a 20 to 30° climbout angle
is attained. An alternate maneuver that may be used
is accomplished by performing a 4.0-G banked turn
using a 60 bank angle. The combination of bank angle
and G-force will produce a climbing turn - not a level
turn. The aircrew must consider fuze arming.

Rocket Launch

The Safe Escape Tables state the minimum launch
altitudes above ground level required for safe escape
from the fragments of the 2.75-inch FFAR with the
MK 1 warhead and the Ml 51 warhead. The minimum
launch altitudes are based on a pullout acceleration
of 4.0 G obtained in 2 seconds used to attain a 10°
climb angle.

DETERMINATION OF MINIMUM ACCEPTABLE
RELEASE ALTITUDE

The vertical drop to fuze arming, minimum recovery
altitude, and bomb fragmentation envelope clearance
must all be considered in the determination of the
minimum acceptable release conditions. The altitude
or vertical drop required for each of these param¬
eters should be determined from the data listed in
the safe escape and fuze arming tables. The greatest
value is the minimum release altitude for the fuze,
dive angle, and airspeed conditions being considered.

5-6

Change 8

T.O. 1F-4C-34-1-1

WARNING

• The aircrew must determine the minimum
ground clearance.

•When the FMU-30/B fuze is used with the
BLU-31/B land mine, minimum release al¬
titudes which will provide safe escape from
bomb fragments for instantaneous or contact
bursts should be selected. This is required
to protect the aircraft and aircrew in the
event of a premature bomb detonation at in¬
itial impact. Refer to Safe Escape, figure
6-14.

• For BLU-31/B land mine shapes, the tra¬
jectory angle at impact should be in excess
of 15° to preclude ricochet.

IMPACT VELOCITY TABLES

Impact striking velocity data for the BLU-31/B land
mine is provided in T.O. 1F-4C-34-1-2. The tables
provide the striking velocity of the weapon in feet per
second for various dive angles, release true air¬
speeds, and release altitudes above target.

FUZE SAFE ARMING TIME REQUIRED

The objective of the following discussion is two-fold:

a. Point out the wide variation in required safe
escape distances and safe fuze arming times for the
various release conditions, release modes, and es¬
cape maneuvers.

b. Emphasize the importance of a judicious selec¬
tion of fuze safe arming times during mission plan¬
ning where VT or impact fuzes are involved. The
fuze arming times, which are required to assure
safe escape from premature airbursts (or earlier-
than-intended impact bursts), vary widely as a func¬
tion of release conditions (level or dive, low altitude
or high altitude) and release modes (single, pairs,
salvo, or timed ripple). The required safe arming
times provided in figure 6-16 for various GP bombs
are listed as a function of release conditions and
escape maneuvers. For clarity, an illustration of
the delivery and escape maneuver profile for each
type of release and escape maneuver is also pre¬
sented.

DETERMINATION OF FUZE SAFE ARMING TIMES
VT Fuzed Munitions

When using proximity fuzes with GP bombs, safety
considerations require that the fuzes be kept unarmed
until the releasing aircraft has attained an adequate
distance from the munition to assure safe escape.

WARNING

Observance of this safety consideration is
absolutely mandatory to assure that the de¬
livery aircraft will not be hit by lethal frag¬
ments from its own munition in the event of
a premature detonation at the expiration of
the fuze arming time.

hi the determination of the VT fuze safe arming time
setting, the value selected should be equal to or
greater than the required safe arming time value
shown in the table for the desired release condition,
release mode, and escape maneuver.

Impact Fuzed Munitions

Ordinarily, premature airburst detonations of impact
fuzed munitions are not anticipated. However, to
protect the aircraft and aircrew from any earlier-
than-intended burst, fuze safe arming time settings,
which will assure safe escape, should be employed
with impact type fuzes (as well as VT fuzes) whenever
operational considerations will permit this course of
action. Use of this procedure would help protect the
aircraft and aircrew in the event of an inadvertent low
altitude release as well as any premature airburst.

WARNING

If operational considerations and the range of
available fuze arming time settings require
the selection of settings which will not assure
safe escape from an earlier-than-intended
burst, the aircrew should be briefed to care¬
fully observe the appropriate minimum re¬
lease altitudes and recovery maneuvers re¬
quired for safe escape.

As an additional safety precaution, whenever opera¬
tional considerations require the use of fuze arming
time settings which will not assure safe escape from
a premature burst, the aircrew should be briefed to
execute a 4.0 G pullup or banked turn escape maneu¬
ver immediately after release.

WRCS DRAG COEFFICIENTS (CB)

The drag coefficient entered in the WRCS control
panel for the dive toss delivery mode (F-4D/E air¬
craft) is listed in figure 6-17. The drag coefficient
(Cb) is a bias factor that is analytically established
to equate the computer bomb trajectory to the actual
bomb trajectory. This drag coefficient value is not
the mathematical drag coefficient of the bomb. The
drag coefficient values and bias settings are provided
in figure 6-17. The ground crew must set the Ballis¬
tic Computer (CP805/ASQ-91) located in door 19.
When Ve is changed, the drag coefficient will change.
Each drag coefficient is optimized for the conditions
listed.

5-7

T.O. 1F-4C-34-1-1

Figure 6-17 presents the drag coefficients for the
CBU-24, -29 series Dispenser and Bomb. These Cg
values are presented as a function of the following
parameters:

a. Pullup acceleration: 3.0 G, 4.0 G, 5.0 G and
6.0 G. This data assumes that the pullup is initiated
immediately after pickle and that the pullup G is at¬
tained 2 seconds after pickle.

b. Dive angle: 15°, 30' and 45\

c. Slant range at time of pickle: 20, 000 ft, 15, 000
ft. and 10 , 000 feet.

EXPOSURE TIME CHART

DIVE BOMBING

The exposure time chart for dive bombing (figure
6-18) provides the time in seconds that the aircraft
will be below a given altitude for a 45° dive delivery
followed by a 4 or 5 G pullout to a 30° climb.

LOFT BOMBING

The exposure time chart for loft bombing (figure
6-18) is provided as an aid to mission planning, for
a loft bomb delivery, in determining tactics required
in a defended area. The time that the aircraft is ex¬
posed above various altitudes is given in seconds.
The chart is computed for a 300-foot approach alti¬
tude AGL; for altitudes other than 300 feet, add the
difference to the exposure time altitude given on the
chart.

LOFT BOMBING WIND CORRECTION

The loft bombing wind correction chart (figure 6-19)
is used to correct the pullup timer setting for range-
wind (headwind or tailwind) and for the wind effect on

the R 2 + R 3 range (range from pullup to bomb impact).

The sample problem illustrates the use of this chart.

WRCS BALLISTIC DATA (F-4D/E)

The WRCS ballistics data for the dive toss bombing
mode 3 , 6 , 8 , and 12 -bomb ripple release, and for
GP bombs, are presented in figure 6-20. Dive Toss
Bombing data for the MK 20 Mod 0 Rockeye II is
presented in figure 6-21. For WRCS ballistic data
for the CBU-24, -29, -49 Dispenser and Bomb, re¬
fer to T.O. 1F-4C-34-1-1A, section VI.

The WRCS ballistic data is presented as a function of
the following parameters:

a. Pullout acceleration: 2.0 G, 3.0 G, and 4.0 G
obtain 2 seconds after pickle.

Note

The ballistic data is based on the assumption
that the pullup maneuver is initiated immedi¬
ately after pickle and that the pullup G is at¬
tained 2 seconds after pickle.

| b. Release interval: 0.06, 0.10, and 0.14 second.

c. True airspeed at time of pickle: 450, 500, 550,
and 600 knots.

d. Dive angle at time of pickle: 20°, 30°, and 45°.

e. Slant range at time of pickle: 10, 000 ft, 15, 000
ft, and 20,000 ft.

The following data is obtained from the tables:

a. Altitude above target at the time of pickle is
computed as a function of the dive angle and slant
range.

Note

The following data is presented for the mid¬
dle bomb in ripple release.

b. The time from pickle to middle bomb release in
seconds.

c. The release altitude of the middle bomb in feet.

d. The release angle of the middle bomb in de¬
grees, measured from horizontal ( 0 °) where nega¬
tive is below the local horizontal.

e. The time of fall from release to impact of the
middle bomb.

f. The pattern length of 3, 6 , 8 and 12-bomb ripple
release. To approximate the pattern length for less
than an eight-bomb ripple, divide the eight-bomb
stick length (S) by seven (S/7), and then multiply by
the number of bombs, minus one bomb, to be re¬
leased (N-l).

BLU-66/B (CBU-46/A) LEFT
DEFLECTION

The characteristic of the BLU- 66 /B bomb causes
the trajectory to shift to the left at an approximate
6:1 ratio. Refer to figure 6-22.

BLU-45/B (CBU-33/A) IMPACT
LATERAL DISPLACEMENT

When the CBU-33/A is carried on the shoulder po¬
sitions of either MER or TER, the BLU-45/B im¬
pact pattern will be displaced laterally in the di¬
rection of the side ejection. The magnitude of this
lateral displacement, which is induced by an effec¬
tive lateral munition ejection velocity component of
approximately 14 ft/sec (20 x sin 45°), is indicated
in figure 4-23. The quantities listed are measured
from the point of ejection and cover the range of re¬
lease conditions provided in the CBU-33/A bombing
tables in T.O. 1F-4C-34-1-2.

BLU-49/B (CBU-38/A) IMPACT
LATERAL DISPLACEMENT

When the CBU-38/A is carried on the shoulder po¬
sitions of either MERs or TERs, the BLU-49/B im¬
pact pattern will be displayed laterally in the direc¬
tion of the side ejection. The magnitude of this
lateral displacement in feet is induced by an effective
lateral munition ejection velocity component of ap¬
proximately 44 ft/sec (62 x sin 45°), as indicated in
figure 6-24. The lateral displacement distances
listed are measured from the point of ejection and
include the release conditions provided in the CBU-
38/A bombing tables in T.O. 1F-4C-34-1-2.

5-8

T.O. 1F-4C-34-1-1

S*/

BOMBING TABLES

Note

The bombing tables (ballistic tables) are con¬
tained in T.O. 1F-4C-34-1-2. Classified bal¬
listic tables are presented in T.O. 1F-4C-34-
1-2A. Following the table of contents in sec¬
tion VI of this manual is a list of all tables
contained in the dash-two manuals.

WARNING

The aircrew must establish the minimum re¬
lease altitude for safe escape and terrain
avoidance.

SINGLE BOMB RELEASE

The following data can be obtained from the bombing
tables for a specific release true airspeed, release
altitude above target and dive angle:

a. Bomb range in feet.

b. Time of flight of the bomb in seconds.

c. Slant range from release to bomb impact in
seconds.

d. Bomb impact angle in degrees.

e. Sight depression from flight pathinmils. (Fuse¬
lage angle of attack must be added to obtain the opti¬
cal sight depression except when the sight is pitch
stabilized.)

f. Wind correction factors: headwind and tailwind
in mils per knot of wind: and crosswind for a drift¬
ing aircraft and/or a crabbing aircraft (level release
in feet per knot of wind). Refer to Wind Correction
for a description of wind factor application.

Note

For the CBU-1, -2 weapons, the bombing
tables provide a sight depression angle that
will place the impact of the first bomblet
500 feet short of the target.

I For CBU-24, -29, -49, -52 and -58 series dispenser
and bomb, single release; level and dive delivery,
refer to T.O. 1F-4C-34-1-2 where the above data
plus the following data is available.

a. Fuze function time in seconds after release for a
given fuze function altitude,

b. Impact pattern diameter in feet.

Not*

The bomb range and the sight depression
from flight path values are established from
the center of the impact pattern of one dis¬
penser.

RIPPLE RELEASE

Ripple release tables are provided for the following
bombs:

a. Ml 17 GP Bomb.

b. MK 82 LDGP Bomb.

c. MD 83 LDGP Bomb.

d. MK 82 Snakeye Bomb (High Drag)

The following data can be obtained from the ripple
release tables for a specific release true airspeed
dive angle, first bomb release altitude above target,
release intervalometer setting, and number of bombs
released:

a. Range from first bomb released to the center of
the impact pattern in feet.

b. Time of fall of the first bomb in seconds.

c. Release altitude of the last bomb in feet.

d. Pattern length in feet.

e. Sight depression from flight path measured from
the release altitude of the first bomb to the center
of the impact pattern in mils.

f. Wind Correction factors: headwind and tailwind
in mils per knot of wind; and crosswind for a drift¬
ing aircraft and/or for a crabbing aircraft (e.g. MK82
Snakeye 1 level delivery) in feet per knot of wind. Re¬
fer to Wind Correction for a description of wind fac¬
tor application.

LEVEL BOMBING TABLE (LEAFLET BOMB)

The level bombing table is completed for the M129E1
leaflet bomb. A sample problem is not provided for
this delivery mode. The bombing table provides the
bomb range and time of flight for a 3000-foot burst
when released from 4000 feet thru 11, 000 feet (in
1000-foot increments) and released at true airspeeds
of 360 knots thru 560 knots in 20-knot increments.

To determine the bomb range and time of flight for
burst heights other than 3000 feet, determine the
release-to-burst distance. Then, from the bombing
table, select a release altitude that will provide the
same release-to-burst distance (release altitude,
minus 3000 feet burst height, equals release-to-
burst distance). For example:

a. Desired release altitude: 4000 feet.

b. Desired burst height: 1000 feet.

c. Release-to-burst distance: 3000 feet.

4000 ft. minus 1000 ft. = 3000 ft.

d. Obtain the bomb range and time of flight from
the 6000-foot release altitude column.

6000 ft. minus 3000 ft. = 3000 ft.

Bomb RtUau Conditions

The level bombing table includes the following pa¬
rameters:

a. Burst height above target: 3000 feet.

b. Level release velocity TAS: 360 knots thru
560 knots.

c. Release altitude above target: 4000 feet thru
11,000 feet.

Change 5

5-9

T.O. 1F-4C-34-1-1

The following data are obtained from the level bomb¬
ing table:

a. Bomb range from release to burst, in feet.

b. Bomb time of flight from release to burst, in
seconds.

LOFT BOMBING TABLES

| GP Bombs, BDU-33/B, A/B, B/B

The loft bombing tables include the following param¬
eters :

a. Target density altitude: -4000 ft., -2000 ft.,
zero ft., 2000 ft., 4000 ft., 6000ft., and 8000 ft.

b. Power Setting: full military power selected at
pullup.

c. Aircraft gross weight at pullup: 42, 000 and
48, 000 pounds, or 36, 000 and 42, 000 pounds.

d. Release angle: 20° thru 50° in 2° increments.

e. Approach altitude AGL: 300 ft., 1000 ft., 3000
ft., and 5000 ft.

f. Approach true airspeed: 500, 550, and 600 knots.

g. Pullup acceleration: 4 G obtained in 2 seconds.

The following data are obtained from the tables:

a. Release altitude above target in feet.

b. Time from pullup to release in seconds.

c. Low angle release gyro setting in degrees.

d. Range from pullup to bomb impact in feet.

e. Time from bomb release to bomb impact in
seconds.

CBU-24, -29, -49, -52, and 58 Series Dispensers
and Bombs

Note

I The level and dive bombing tables for the

CBU-24, -29, -49, -52 and -58 are contained
in T.O. 1F-4C-34-1-2.

The loft bombing tables include the following param¬
eters and are contained in T.O. 1F-4C-34-1-2.

a. Target density altitude: -4000 ft, -2000 ft,
zero ft., 2000 ft., 4000 ft., 6000 ft., and 8000 ft.

b. Power setting: Full military power selected at
pullup.

c. Aircraft gross weight at pullup: 42, 000 pounds
and 48, 000 pounds.

d. Release angle: 30° and 40°.

e. Approach altitude AGL: 300; 1000; 3000; and
5000 feet.

f. Approach true airspeed: 500, 550 and 600 knots,

g. Pullup acceleration 4.0 G obtained in 2 seconds,

h. Ripple release intervals: 100 and 140 milli¬
seconds.

i. Number of bombs released: eight,

j. Fuze function altitude: 2500 feet AGL.

k. Weapon: CBU-24, -29, -49 series.

The following data are obtained from the tables:

a. The release attitude of the first bomb in degrees
is the value that is set in the low angle release gyro.

5-10 Change 5

The time from pullup to release value on the follow¬
ing line is increased by the ripple interval time used,
and the resulting release angle is provided on the
same line. Eight lines are provided for each release
condition; one line for each bomb ripple off. If less
than eight bombs are to be released, use the corre¬
sponding time from pullup to release. Establish the
following parameter of the first and last bomb off:

b. Release altitude above target in feet AGL.

c. Time from pullup to release in seconds.

d. Fuze function time setting required to obtain a
2500-foot fuze function altitude, in seconds.

e. Time from pullup to impact (in seconds) of the
BLU-26/B or BLU-36/B or BLU-59/B.

f. Range from pullup to the center of the impact
pattern, in feet.

ROCKET LAUNCH AND GUN FIRING
TABLES

The 2.75-inch FFAR and 20mm ballistic tables pre¬
sent the sight settings as a function of density alti¬
tude, calibrated airspeed, and aircraft gross weight.
Aircraft angle of attack and parallax correction is
included in the sight setting value.

The launch tables are applicable to all rocket launch¬
ers, including the SUU-20/A, A/A bomb and rocket
dispenser, suspended from pylon or MER/TER.
Seperate tables are required when the rocket war¬
head affects its trajectory; the launch tables are
divided as follows:

a. MK-1 and MK-5 warheads and includes the prac¬
tice rocket with an inert rocket head.

b. M151 warhead.

c. WDU-4A/A warhead.

Based on 4.0 G pullout, the aircraft should clear the
fragment envelope during recovery for all launch
conditions listed in the launch tables.

The gun firing tables are applicable to the SUU-16/A,
-23/A gun pods and the F-4E nose gun. The condi¬
tions listed in the tables provide a ground clearance
of at least 50 feet, based on a 4.0 G pullout attained
2.0 seconds after release or firing altitude. The AC
should note that dive angle, firing altitude, and fir¬
ing airspeed has a negligible effect upon the sight
setting and therefore may be disregarded. The sight
setting is affected by angle of attack, but to a lesser
degree than angle of attack affects the 2.75-inch
rocket. This is due to the difference in time of flight
between the 20mm projectile and rocket. Note also
that range and the wind corrections change with time
of flight which is affected by dive angle, altitude
above target, and airspeed. The outboard guns are
harmonized at a slant range of 2250 feet. That is,
the outboard gun pods are toed-in to permit the 20mm
projectiles to converge at a point 2250 feet forward
of the aircraft. The centerline gun pod is aligned
with the centerline of the aircraft.

The rocket launch and gun firing tables include the
following parameters:

a. Target density altitude: sea level, 5000 feet, and
10, 000 feet.

T.O. 1F-4C-34-1-1

b. Aircraft gross weight: 36, 000; 38, 000; 40, 000;
42, 000 and 44, 000 pounds.

c. Altitude above target: 200 to 12,000 feet.

d. Launch or firing calibrated airspeed (CAS): 400
to 600 knots.

e. Dive angles: 10° to 60°.

The following data are obtained from the rocket
launch and gun firing tables:

a. Sight setting in mils.

b. Slant range in feet.

c. Horizontal range in feet.

d. Wind correction factors in feet per knot of wind
and mils per knot wind. Rangewind and crosswind
correction factors are the same.

e. Time of flight in seconds.

FLARE DISPENSING TABLES

In T.O. 1F-4C-34-1-2, flare dispensing tables are
provided for the SUU-25/A, SUU-25B/A, and SUU-
42/A dispensers containing either the MK 24 flare,
the LUU-l/B marker, or LUU-2/B flare.

The tables provide the minimum release altitude
AGL for flare burnout at impact. The desired burn¬
out altitude AGL must be added to the minimum re¬
lease altitude AGL to determine the actual release
altitude AGL. The flare dispensing table also pro¬
vides the horizontal distance traveled and vertical
drop of the flare prior to ignition. The flare ejection
fuze delay time and the flare ignition fuze delay time
is set according to mission requirements and the
data on the flare dispensing table. Rangewind cor¬
rection and crosswind correction should be applied
using a wind factor of 150 feet per knot of wind.

MLU-32/B99 FLARE (BRITEYE) LEVEL
RELEASE TABLE

The horizontal and vertical distance travel of the
MLU-39/B99 flare prior to flare ignition is given in
the table. The desired burnout altitude AGL, plus
1500 feet for burn time, must be added to the verti¬
cal drop distance obtained from the table to deter¬
mine the minimum level release altitude AGL.

DIVE BOMBING AND LOW LEVEL BOMBING SAMPLE PROBLEM

MISSION CONDITIONS

The following sample problem assumes MK 82 Snake-
eye retarded release conditions. The precise plan¬
ning may not be required for other bombing mis¬
sions, depending on the accuracy required. The
sample problem follows the order outlined in the
mission planning form (figure 6-1) to illustrate the
computations required to determine the pattern
length of a six-bomb ripple release, and the effect
of side-ejection error induced by the MER and TER
bomb racks. The ripple release mode for the land
mine is used only for illustrative purposes. If ex¬
ternal tanks are to be carried, the appropriate data
would be entered in (4a). Item (4e) is the total ex¬
ternal weight including pylons and adapters and
racks, and the outbound drag index.

Compute the fuel remaining over target (6): Deter¬
mine the airplane gross weight over target:

Airplane operating weight (5)
External weight (4e)

Fuel remaining over target (6)
Airplane gross weight over
target (7)

31.100 lbs.
9619 lbs.
4281 lbs.
45,000 lbs.

Obtain the target elevation (8) and plot the true course
to target: complete items (9) and (10). The minimum
aircraft recovery altitude above ground level (AGL)
will be established by the major command.

RELEASE CONDITIONS

Safe escape and fuze arming (11) must be considered
when using the GP bombs and the 2.75-inch rockets.
Refer to figures 6-11 thru 6-14. The release al¬

titude AGL (16) or (28) must be greater than the min¬
imum release altitudes required for safe escape and
fuze arming (11). Also, check the fuze arm delay
setting plus the fuze tolerance to ensure that the set¬
ting is LESS than the bomb time of flight; then, check¬
off item (11c). Item (lid) is applicable only to the
BLU-31/B Land Mine with the FMU-30/B fuze.

Weather forecast data provides the following:

a. Forecast target temperature (12): 5°C.

b. Wind velocity (24): 360' True/30 knots.

The following charts are used to determine items (15)
(19), (20), (21), and (23).

a. Dive Recovery charts, figure 6-2.

b. Altimeter Lag chart, figure 6-8.

c. Angle of Attack chart, figure 6-3.

d. Airspeed Conversion chart, figure 6-4,

e. Altimeter Position Error Correction (F-4C/D).
figure 6-7.

The calibrated airspeed release velocity (13), dive
angle (15), and release altitude (16) are selected and
entered in the form. True airspeed is obtained from
figure 6-4 as a function of CAS, forecast tempera¬
ture, and forecast pressure altitude at release alti¬
tude. If forecast pressure altitude is not available,
release altitude MSL (17) may be used. If the ripple
release mode is used, complete item (18). Use the
dive recovery charts to find the altitude lost during
pullout (19). The recovery altitude must be greater
than the minimum recovery altitude (10). Subtract
the altitude lost during pullout from the Release
Altitude AGL (16).

1500 feet minus 323 feet = 1177 feet

5-11

T.O. 1F-4C-34-1-1

(F-4C) (F-4D)fiF-4E)j

Sheet 1 of 7

MISSION PLANNING FORM
NONNUCLEAR

MISSION CONDITIONS

1. Delivery and Release Mode .

2. Munitions

0/tff .7 \

Weight

lbs. Drag

3. FUZING:

a. Fuze.

b. Arming Delay.(Tolerance ±

J6%. 1 =

c. Functioning Delay

4. Drag Index and External Weight:

a. Outboard:

b. Inboard:

c. Centerline:-

. w

d. Fuselage:

e. Totals:

;e: -A. ,

5. Airplane Operating Weight

6. Fuel Remaining Over Target:

-T. wgt.
. T. wgt.
. T. wgt.
T. wgt.

T. wgt.

7. Airplane Gross Weight Over Target (Add: #4e, #5, and #6)

lbs, Drag Index.
lbs, Drag Index .
. lbs, Drag Index.
. lbs, Drag Index,
lbs ,|Drag^ndej^
pounds

pounds

CTUV pounds

8. TARGET DATA:

a. Altimeter setting over target.

b. Target Elevation MSL.

c. Target Temperature.

d. Target Pressure Altitude.

e. Target Density Altitude (forecast or fig 6-5 )

zL zUL in. Hg.

ISO feet

JH _ C

Op _^eet

li£u£t:ieei

9. Approach Course to Target.

10. Minimum Aircraft Recovery Altitude AGL. (Check #16 minus #19).

(To be established by Major Command)

S'QZ?

op-130 -120 -110 -100 -90 80 -70 -60 -SO -40 - 30 - 20 -10 0 10

■ ■ i min iilim I n h | 11 |j [ i U l | 111 i j l,| II 111 IJ L .. I I I I ■ I I I I I I I • I I ' I ■

_20 -10 0 10 70 30 40 SO 60 70 80

90 100 HO 120 130 140

10 M M «

5-12

T.O. 1F-4C-34-1-1

Sheet 2 of 7

25. Relative Wind Velocity (fig 6-11)

r PS i

knots 1

Figure 5-3 (Sheet 2 of 3)

F4—34—V—103-2

5-13

MISSION PLANNING FORM
NONNUCLEAR

(F-4C) (F-4D)/(F-4E)

RELEASE CONDITIONS

11. Safe Escape and F'uze Arming:

a. Minimum Release Altitude (AGL) for Frag Clearance
From Safe Escape Table, figure 6-14 or 6-15.
(Ensure that #16 or #28 is greater than #lla)

b. Minimum Release Altitude (AGL) for Fuze Arming .
From Fuze Arming Table, figure 6-13, 6-15 or 6-16.
(Ensure that #16 or #28 is greater than #llb)

c. Check Fuze Arm Delay Setting plus Fuze Tolerance,

is LESS THAN Bomb Time of Flight.

d. Impact Velocity of BLU-31/B with FMU-30/B Fuze
(less THAN 900 fps)

12. Forecast Temperature at Release Altitude MSL. 3 °q

13. Calibrated Airspeed Release Velocity. 435T knots

14. True Airspeed Release Velocity (Vp).

15. Dive Angle. 30 degrees

16. Release Altitude AGL (Must be greater than #11). ^2.0 OQ feet

17. Release Altitude MSL (#8b + #16). 22.Q-S'C> feet

18. Ripple Release Interval (I R ) Setting: (.06) (.10) . 1 40 sec

19. Altitude Lost During Pullout.(3.0G ^(4.0 Gj)(5.0G). / /-S"3 f eet

20. Altimeter Lag.SPC off S2Q spc ON SS~ feet

21. Altimeter Position Error Correction (F-4C/D).SPC ON & a foot

22. Indicated Release Altitude MSL (Add: #17, #20 & #21) . . |sPC^OFF3£^JsP^^^O^fee^

23. Angle of Attack from zero sight line (fig 6-3) . ^ 2 m ils

0 10 20 30 <0 SO Ml n 10

WIND VALUES KHC

24. Forecast Wind Velocity .

26. Rangewind Component (nead)Jjterftf .

27. Crosswind Component (left) (pigfit) .

3FO

_°True

_ knots

3/0

- knots

34-

_ fps

. knots

. fps

- knots

T.O. 1F-4C-34-1-1

(F-4C) (F-4D)/(F-4E)

MISSION PLANNING FORM
NONNUCLEAR __

Sheet 3 of 7

DIVE AND LOW LEVEL BOMBING CONDITIONS (SINGLEVfRIPPLE)

* 28. (Ripple Rel) Release Alt of Last Bomb (Must be greater than #11)
From Ripple Table or, #16 minus [ (I R ) (1.69) (V R ) (Sin 9) (N-l)J

29. Bomb Range (not required if ripple table is used).

i4i?

a. First Bomb (fr. single table)

b. Last Bomb (Interpolate table).
30. Bomb Time of Flight

*a. First Bomb (fr. single or ripple table).

b. Last Bomb (interpolate table)

. 7.// seconds

seconds

* 31. Ripple Pattern Length for ^ —bombs from ripple table or.'.. feet

P.L. = [(I R ) (1.69) (V R ) (Cos 0) (N-l)] - AR

* 32. Range from First Release to Center of Ripple Pattern.feet

(fr. ripple table or, #29a plus one-half #31)

* 33. Sight Depression from Flight Path (fr. table or Sight Depression charts).^

34. Sight Setting (no wind) (#23 + #33).^53^nil^J

* 35. Headwind Correction Factor (Add) fr. table .mil/knot

_ 2

* 36. Tailwind Correction Factor (Subtract) fr. table.. '—A- mil/knot

i j o

* 37. Crosswind Correction Factor fr. table.. . . ft/knot

n n TT_-_1 A 1 -/nln/rln 3SO °True 396 _ feet

* 37. Crosswind Correction Factor fr. table

38. Upwind Aimpoint (single point offset)..— True J .. -

(Multiply #24 by #37)

39. Relative Wind Vector:

a. Rangewind Correction.(+H) ^feet a or (+H)

tMultiply #26 by #35 or #36 and #37) / , . /

n__i ~A _ . . . ^ _

(Multiply #26 by #35 or #36 and #37; s

b. Crosswind Correction.(left) (rj^ht)

(Multiply #27 by #37)

40. Sight Setting Corrected for Rangewind (#34 * #39a).

Zo4

41. Side Ejection Impact Distance (feet) and Release Sequence (if applicable) fig. 6-6.

IMPACT LEFT —-;-► IMPACT RIGHT

STATION 2

Sequence
Error - ft.

STATION 8

Sequence
Error - ft.

STATION 1

STATION 5

STATION 9

Sequence
Sequence
Error - ft.

♦ Value can be obtained from Ripple Release Table.

F4-34-V-103-3

Figure 5-3 (Sheet 3 of 3)

5-14

T.O. 1F-4C-34-1-1

To determine the indicated release altitude (22), al¬
timeter lag should be added to release altitude MSL.
In addition to altimeter lag, altimeter position error
should be considered: F-4C/D, figure 6-7.

SPC Off

SPC On

Release altitude

2250

2250 feet

MSL (17)

Altimeter lag (20)

820

55 feet

Altimeter position
error (21)

Indicated release

0 feet

3070

2305 feet

altitude (22)

Use the angle of attack chart to find the angle of at¬
tack in mils (23). Note how angle of attack becomes
smaller as the bombs are released and/or as fuel is
used, approximately one mil per 1000-lb. bomb.

Use the following given conditions.

Note

If release pressure altitude is not known, re¬
lease altitude MSL may be used (17).

Given: a. Release velocity CAS (14): 435 knots

b. Gross weight at release (7): 45,000 pounds

c. Dive angle (16): 30°

Find: Angle of attack (23): 22 mils

WIND VALUES

Use the relative wind vector chart figure 6-11 to de¬
termine the rangewind and crosswind components,
based on forecast wind velocity (24). Use the knots-
to-feet per second conversion scale, located on the
mission planning form.

DIVE AND LOW LEVEL BOMBING
CONDITIONS

RIPPLE RELEASE COMPUTATIONS
With Ripple Release Tables

When ripple release tables are provided in T.O. 1F-
4C-34-1-2, ripple release computations are reduced
to a minimum. The following data are obtained from
the tables for a given release interval and number of
bombs released (figure 5-4) and entered in the sam¬
ple planning form figure 5-3.

a. Release altitude of the first bomb (16) and the
last bomb (28).

b. Bomb time of flight for the first bomb (30a).

c. Range from first release to the center of the
ripple pattern (32).

d. Sight depression from flight path to the center
of the ripple pattern (33).

e. Wind correction factors (35), (36), and (37).

The bomb range (29) of the first and last bomb is not
required since these values are used to establish the
pattern length and sight depression when ripple re¬
lease tables are not available. The bomb time of

flight for the last bomb (30b) should be determined
and compared with the fuze setting plus tolerance to
ensure that the fuze setting is LESS. To determine
the time of flight of the last bomb (30b) interpolate
from the bombing table.

Without Ripple Release Tables

Note

The values used in the following example are
not applicable to the MK 82 Snakeye bomb and
the sample planning form figure 5-3. The
values in figure 5-5 are used to show ripple
release computations when ripple release
tables are not available.

The following computations are not required for
single bomb release, or if the pattern length and
mid-pattern sight setting are not required. However,
the release altitude of the last bomb (28) should be
computed to determine that the minimum recovery
altitude, bomb fuzing, and safe escape requirements
are satisfied.

To determine the release altitude of the last bomb
(28), subtract the product of [ (lR)(1.69)(VR)(Sine 0)
(N-l)] from the release altitude of the first bomb
(16), 1500 feet. Check safe escape and fuze arm¬
ing (11).

Ir = Release interval setting: 0.14 second.

Vr = True airspeed release velocity: 400 knots.

0 = Dive angle: 15°

Sine 0 = 0.25882 (obtained from figure 6-9).

N = Number of bombs in the ripple release: 6.

N-l = (6-1) = 5.

Release altitude of first bomb

1500 ft. minus [ (0.14)(1.69)(400)(0.25882)(5) ] =
1396 ft. release altitude of last bomb.

To determine the length of ripple pattern, the range
of the last bomb must be computed. Interpolate be¬
tween the bomb ranges listed for 1500 feet and 1000
feet; for the bomb range of the last bomb released
from 1396 feet, use 1400 feet.

3533 ft. range of first bomb minus 2603 ft. range
of bomb released from 1000 feet = 930 ft.

Divide the difference by 5 to determine the bomb
range per 100-foot release altitude.

930 ft. -j-5 = 186 feet per 100 ft. of release altitude

The range of the last bomb release from 1396 feet
(or 1400 feet rounded off) equals:

3533 ft. - 186 ft. = 3347 ft. range of last bomb.

5-15

T.O. 1F-4C-34-1-1

RIPPLE RELEASE TABLES

S' BOMB. GP. 500-lb. MK 82 (SNAK.EYE 1)
1? BOMB RIPPLE

RELEASE INTERVAL 140 MILLISECONDS

HIGH DRAG

RANGE

TIME

RELEASE

PATTERN

SIGHT DEP

WIND CORRECTION

DIVE

TAS

ALT

TO CENTER

FALL

ALT

LENGTH

FROM

FACTORS

angle

ABOVE

FIRST

last

FLIGHT

TGT

PATTERN

BOMB

PATH

head tail

CROSS

DEG

KTS

SEC

MILS

mils/knot

FT/KT

400

1700

2284

6.76

1180

461

119

2.50 -2.35

11.4

400

1800

2366

7.21

1280

489

130

2.59 -2.43

12.2

400

1900

2444

7.66

1380

514

140

2.68 -2.51

12.9

400

2000

2516

8.11

1480

539

151

2.77 -2.59

13.7

400

2100

2585

8.56

1580

560

162

2.86 -2.67

14.4

400

2200

2649

9.01

1680

580

172

2.95 -2.76

15.2

4 00

2300

2707

9.45

1780

603

184

3.04 -2.84

15.9

400

2400

2766

9.89

1880

617

194

3.12 -2.91

16.7

400

2500

2819

10.33

1980

632

205

3.21 -2.99

17.4

400

2600

2870

10.76

2080

648

215

3.29 -3.07

18.2

400

2700

2917

11.20

2180

663

226

3.38 -3.15

18.9

400

2800

2961

11.63

2280

672

237

3.46 -3.22

19.6

400

2900

3005

12.06

2380

685

247

3.54 -3.30

20.4

400

3000

3046

12.48

2480

697

257

3.61 -3.37

21.1

C 1 1

1^1-

ia.4 ■■■

— 46 -

440

2000

2620

7.81

1428

556

131

2.53 -2.38

13.2
10«9-

—30 —

440

—0106-

2200

2764

8.71

1628

606

X ~ X

151

2.71 -2.53

14.7

440

2300

2830

9.15

1728

629

162

2.79 -2.61

15.4

440

2400

2892

9.59

1828

650

172

2.87 -2.69

16.2

440

2500

2950

10.03

1928

671

182

2.95 -2.76

16.9

440

2600

3005

10.47

2028

689

192

3.04 -2.84

17.7

440

2700

3057

10.90

2128

705

202

3.12 -2.91

18.4

440

2800

3106

11.33

2228

721

213

3.19 -2.98

19.1

440

2900

3153

11.76

2328

734

223

3.27 -3.06

19.8

440

3000

3197

12.19

2428

748

233

3.35 -3.13

20.6

F4—34—V—112

Figure 5-4

5-16

T.O. 1F-4C-34-1-1

DIVE BOMBING TABLE

DIVE

TAS

ALT

ANGLE

ABOVE

TGT

DEG

KTS

360

1000

380

1000

400

1000

460

10 00

480

1000

500

1000

520

1000

540

1000

560

1000

580

io on

02 Jr

360

10 JO

1396

1500

jUit&u

15 '

380

1500

400

1500

420

1500

_ 1500

k 15^-

BOMB

RANGE

2478

^2603 -
2660
2712
2762
2808
2851
2891
2929
2964
2997
3028

3347

3337

kB&

3622
3707

SINGLE RELEASE

THIS TABLE IS USED TO SHOW RIPPLE RELEASE
COMPUTATION WHEN RIPPLE RELEASE TABLES
ARE NOT AVAILABLE.

TIME

SLANT

RANGE

IMPACT

ANGLE

SIGHT DEP
FROM

WIND CORRECTION

FACTORS

FLIGHT

FROM

REL

DEG

FLIGHT PATH

HEAD

TAIL

CROSS

SEC

MILS

MILS/KNOT

FT/KT

4.42

2672

125

1.09

-1 .03

7.5

4.30

2733

2788

116

108

1.01

0.94

-0.96

-0.90

7.3

7.1

2842

101

0.88

-0.84

6.9

3.97

2890

0.83

-0.80

6.7

3.87

2937

0.78

-0.75

6.5

3.77

2981

0.74

-0.71

6.4

3.68

3021

0.70

-0.68

6.2

3.59

3059

0.67

-0.64

6.1

3.50

3095

0.64

-0.6 1

5.9

3.42

3128

0.61

-0.59

5.8

3. 34

3159

0.58

-0.56

5.6

3.27

S-45+-

6.04

3659

60 d

163 /' C

5.90

<G.7?Z0

3751

3838

152 /

CT42~S

1.10

<H22>

-1 .05
CrO.92>

10.0

dID>

^5.64

3920

133

0.96

-0.92

9.5

/ 5.51

3999

125

0.90

-0.86

9.3

4073

118

0.85

^.81

A 9.J._

s/ hrmd-

—

^ F4-34-V-104

Figure 5-5

Interpolate the bombing table to determine the time
of flight of the last bomb (30b).

To determine the ripple pattern length (P.L.) for six
bombs, subtract the difference between the range of
the first and last bomb ( A R), from the product of
[(Ir)(1.69)(V r )(Cos 6 )(N-1) J.

P.L. = Pattern Length in feet.

Ir = Release interval setting: 0.14 second

Vr = True airspeed release velocity: 400 knots.

0 = Dive angle: 15 degrees.

Cos 0 = 0.96593 (obtained from figure 6-7).

N = Number of bombs in the ripple release: 6.

N-l = (6-1) = 5.

A R = Range of first bomb, minus range of last
bomb: 186 feet.

P.L. = [ (0.14)(1.69)(400)(0.96593)(5) ] - 186 ft.

P.L. = 200 feet.

To determine the sight depression angle from flight
path to the center of the ripple pattern (33), enter the
applicable sight depression chart with the range from
release of the first bomb to the center of the ripple

pattern (32); this range is determined by adding one-
half of the ripple pattern length to the range of the
first bomb.

3533 ft. range of first bomb plus (200 - 2) = 3633 ft.
Enter the 15° dive, sight depression chart with:

a. Range from release to target (32): 3633 ft.

b. Release altitude AGL (17): 1500 ft.

c. Read sight depression angle from flight path (33):
139 mils.

To determine the sight setting for no-wind (34), add
the angle of attack from zero sight line (23).

139 mils + (-2 mils) = 137 mils.

Rangewind correction can be made by adjusting the
sight setting or by estimating an aim point based on
the rangewind effect (for a headwind the bomb will
hit short of the target).

(1.0 mil/knot) (20 knots headwind) = 20.0 mils,
or

(9.7 ft./knot)(20 knots headwind) = 194 ft. short of
target

Therefore add 20 mils to the no-wind sight setting
or aim 194 feet long.

5-17

UNCLASSIFIED

T.O. 1F-4C-34-1-1

Crosswind correction can be made by determining
the wind effect of the bomb, using the crosswind fac¬
tor,

(9.7 ft./knot(23 knots left crosswind) = 223 ft. left.

Note

Crosswind correction is not required for low
level bombing with low drag bombs if the air¬
craft ground track through the target is main¬
tained until release occurs.

The no-wind side ejection error is obtained from fig¬
ure 6-6, side ejection impact distance chart. Enter
the distance that the bomb will be ejected, left and
right of the aircraft flight path, in the mission plan¬
ning form and in the checklist. Select the applicable

aircraft station, enter the chart with the weight of
the bomb (2), project through time of fall (30) curves,
and then project down from the curve applicable to
the MER or TER position (Inboard, Bottom, and Out¬
board to read the lateral displacement of the bomb
from the centerline of the aircraft, left or right.

WRCS DELIVERY MODES (F-4D
AND F-4E)

When the WRCS delivery modes are used, a minimum
of planning should include the following items:

a. Mission conditions, items (1) thru (10).

b. Safe escape and fuze arming (11).

c. Release and jettison limitations from T.O. 1F-
4C-1 Flight Manual.

d. WRCS counter settings (79) thru (83).

ROCKET LAUNCH AND GUN FIRING SAMPLE PROBLEM

ROCKET LAUNCH AND GUN FIRING
CONDITIONS

The rocket launch and gun firing data, items (42)
thru (50), are obtained directly from the tables,
based on the established mission conditions, release
conditions, and wind values outlined in the mission
planning form, figure 6-1. The mission conditions
and release conditions are assigned and determined
by the same procedure outlined for the Dive and Low
Level Bombing sample problem. These procedures
are not repeated here: however, a completed sample
mission planning form (figure 5-6) has been pre¬
pared for the rockets using launch table figure 5-7.

The applicable launch table is selected by establish¬
ing the following conditions:

a. Type of rocket warhead: MK-1 warhead.

b. Target density altitude:

c. Dive angle:

d. Calibrated airspeed:

e. Aircraft gross weight:

The sight setting corrected for rangewind is obtained
by adding the rangewind correction (46) or (47) for
headwind, or subtracting for tailwind, from the no-
wind sight setting (43).

39 mils + 8 mils = 47 mils.

5-18

Sheet 1 of 7

MISSION PLANNING FORM
NONNUCLEAR

MISSION CONDITIONS

1. Delivery and Release Mode

2. Munitions

Weight

pounds

TAIL

3. FUZING

NOSE

a. Fuze

(Tolerance ±

b. Arming Delay

c. Functioning Delay

4. Drag Index and External Weight

a. Outboard:

lbs, Drag Index

b. Inboard:

lbs, Drag Index

c. Centerline

lbs, Drag Index

d. Fuselage

lbs, Drag Index

e. Totals

lbs,|Drag Index

5. Airplane Operating Weight

pounds

6. Fuel Remaining Over Target

pounds

42,000 pounds

7. Airplane Gross Weight Over Target (Add: #4e, #5, and #6)

TARGET DATA:

a. Altimeter setting over target

b. Target Elevation MSL . . .

c. Target Temperature....

d. Target Pressure Altitude. .

e. Target Density Altitude. . .

9. Approach Course to Target

True

Minimum Aircraft Recovery Altitude AGL. (Check #16 minus #19)
(To be established by Major Command)

Figure 5-6 (Sheet 1 of 3)

T.O. 1F-4C-34-1-1

(F-4C) (F-4D)^F-4E^

MISSION PLANNING FORM
NONNUCLEAR

RELEASE CONDITIONS

11. Safe Escape and Fuze Arming:

a. Minimum Release Altitude (AGL) for Frag Clearance. . . .
From Safe Escape Table, figure 6-14, or 6-15.

(Ensure that #16 or #28 is greater than #lla)

Sheet 2 of 7

1800

feet

~-" - “ —-o-- k/A

b. Minimum Release Altitude (AGL) for Fuze Arming. /\M _feet

From Fuze Arming Table, figure 6-13, 6-15 or 6-16.

(Ensure that #16 or #28 is greater than #llb)

c. Check Fuze Arm Delay Setting plus Fuze Tolerance, / )

is LESS THAN Bomb Time of Flight. 1 —L - !

d. Impact Velocity of BLU-31/B with FMU-30/B Fuze

(less THAN 900 fps).—- £ P S

. // °c.

12. Forecast Temperature at Release Altitude MSL

13. Calibrated Airspeed Release Velocity.

knots

14. True Airspeed Release Velocity (Vr).

30 . degrees

15. Dive Angle.

16. Release Altitude AGL (Must be greater than #11)

17. Release Altitude MSL (#8 fe + #16)

2000 feet
2000 feet

(. 10 )

18. Ripple Release Interval (Ir) Setting: (.06)

19. Altitude Lost During Pullout (3.0G)^L0Gj)(5.0G).

20. Altimeter Lag.SPC OFF

(.14).-

800 spc on _.

_sec

1200 feet

5 5 feet

21. Altimeter Position Error Correction (F-4 C/D ) . . . .SPC ON a feet

22. Indicated Release Altitude MSL (Add: #17, #20 & #21 )|spc > OFF^8£0^spC b OI^^^^5^^

/& mils

23. Angle of Attack from zero sight line (fig 6-3)

ppr 0 » » » 9 »

WIND VALUES

KNOTSJ

24. Forecast Wind Velocity.

25. Relative Wind Velocity (fig 6-11)

60 70 8

27. Crosswind Component (left) £pigfit)

350

_°True

knots

3/0

knots

_ fps

knots

_ fps

knots

S» 530 540 550 560 570 580 590 600 6)0 620 630 640 650 660 670 680 690 700 710 720 730 740 750 760 770 780 790

.J.- [ J--L-.pi- 1 p > .. l--p j.l . p. 1 .

KNOTS

FPS.

KNOTS

310 370 330 340 350 360

790 800 DO 820 830 840 850 860 870 880

470 480 490 500 510 520 530 540

370 380 390 400 410 470

900 910 970 930 940 950 960 970 980

430 440 450 460

1000 1010 1020 1030 1040 1050 1060

Hw I wWvm Vt

550

SM S70 580 S90 800 610 610

F4E-34—V-105-2

Figure 5-6 (Sheet 2 of 3)

5-20

T.O. 1F-4C-34-1-1

44. Slant Range

(F-4C)(F-4D/TF-4E)

Sheet 4 of 7

MISSION PLANNING FORM
NONNUCLEAR

ROCKET LAUNCH AND GUWfTRINJ CONDITIONS ^

Rocket Warhead Used: /MK-lMMK-5, Heat) (Practice)(M151)(WDU-4A/A)

42. Time of Flight ... I . .f. ..

43. Sight Setting (no wind)

45. Horizontal Range

46. Wind Correction

A 9 ^
37
3275
33/7

seconds

47. Wind Correction.

48. Upwind Aimpoint (single point offset)
(Multiply #24 by #46)

49. Relative Wind Vector:

a. Rangewind Correction (Multiply #26 by #47) (+H) .

b. Crosswind Correction (Multiply #27 by #46) (left) (right)

o.+

feet per knot
mils per knot

3 SO

50. Sight Setting Corrected for Rangewind (#43 ± #49a) (+H )

LOFT BOMBING RIPPLE RELEASE CONDITIONS

51. Approach Calibrated Airspeed

52. Approach True Airspeed (fig 6-4)

53 , Approach Altitude AGL

54. Indicated Approach Altitude MSL (Add: # 8 b, #53, #21)

55. FIRST BOMB (from table):

a. Release Angle of First Bomb .

b. LOW ANGLE Release Gyro Setting (table)

c. Release Altitude AGL.

d. Time from Pullup to Release (t^)

e. Range from Pullup to Impact (R 2 + R 3 )

f. Time from Release to Impact (t c )(check #llc)

56. Time Required to Ripple_Bombs (#19 times N-l).

(Multiply Interval Setting by number of bombs, minus one bomb).

degrees

degrees]

seconds

Figure 5-6 (Sheet 3 of 3)

5-21

T.O. 1F-4C-34-1-1

75 INCH/tFAR WIT/TMK-lJ»k-5 WARHEAD AND PRACTICE ROCKET
LAU-X LAU-3<Sr—t7fU-59 AND SUU-20 LAUNCHERS
ARGET DENSITY ALTITUDE - MEAN SEALEVEL A-

ALT

TIME

AIRG^TTFaT

GROSS

HEIGHT

- THOUSANDS CF

POUNDS

WIND CORRECTIONS

ABOVE

KCAS

DIVE

(42/

FACTORS

TGT

ANGLE

FLT

SIGHT SETTING

-NrllS

DEG

SEC

NEG

SETTING

INDICATES ELEV

SLANT

range -

FEET

HORIZONTAL RANGE - FT

FT/KT

mil/kt

1500

A0 0

1.62

2913

2917

2921

2497

2 502

2507

1500

44Q

1.59

2912

2915

2918

2496

2500

2504

1500

460

1.56

2914

2916 L
N

2918

2498

2501

O, 2503

2000

400

1.96

3869

3675 0*

3880

3312

3319

3325

2000

440

1.92

3869

3873 V\

3377

3312

3316

/O 3321

2000

480

i. is

T T

3871

3 8 7 4

3877

3314

3318

3321

2000

520

1.85

3874

3877

3879

3318

3321

3324

20 0 C

560

1.81

3876

3880

3882

3323

3325

3327

. 4

2500

400

2.32

48 2 0

4827

4833

4121

4129

4137

. 4

2500

440

2.27

4820

4625

4830

4121

4127

4132

. 4

2500

460

2.23

482h

43 27

4831

4125

4129

4134

2500

520

2.13

4828

4831

4834

4130

4134

4137

2500

560

2.14

4833

4835

4838

4136

4139

4142

2500

600

2.10

4839

4841

4843

4143

4146

4148

• 4

F4-34-V-111

Figure 5-7

LOFT BOMBING SAMPLE PROBLEM

LOFT BOMBING RIPPLE RELEASE
CONDITIONS

Sample mission planning form (figure 5-8) is pro¬
vided to establish mission conditions, release con¬
ditions, and wind values for this sample problem.

The purpose of the following computations is to es¬
tablish the following:

a. Low angle release gyro setting.

b. Approximate pattern length.

c. Pullup timer setting for no-wind and forecast
rangewind.

d. Aircraft exposure time above a given altitude.

e. WRCS LABS/TGT FIND Rr setting.

Complete sheet 1 of the Mission Planning Form. On
sheet 2, complete item (11c) after the bomb time-of-
flight is determined. Items (11a) and (lib) are not
applicable to Loft Bombing. Also, complete items
(24) thru (27) Target Wind Values if available. To
determine the target density altitude, refer to Alti¬
tude Conversion chart. Enter the chart with target
pressure altitude and target temperature, read tar¬
get density altitude. Density altitude is required to
select the proper set of loft bombing tables. Linear
interpolation between sets of density altitude bombing
table should be accomplished or at least considered.

To obtain the approach true airspeed (52), enter the
airspeed conversion chart (figure 6-4) with the fol¬
lowing conditions and read, 400 knots:

a. Calibrated airspeed approach velocity (51): 395
knots.

b. Forecast temperature at approach altitude (8c):
20 J C.

c. Approach pressure altitude or approach altitude
MSL (target pressure altitude, plus, approach alti¬
tude AGL): 300 ft.

0 ft. + 300 ft. = 300 ft.

Altimeter position error for F-4C/D aircraft with
Static Correction Operating (21) is determined by
reference to figure 6-7. Indicate approach altitude
MSL (54) is the sum of items (8b), (53), and (21).

Select the loft bombing table computed for the follow¬
ing given conditions (figure 5-9):

a. Gross weight of aircraft at pullup (7): 43,330
pounds. Use the table computed for 42, 000 pounds
gross weight.

b. Target density altitude (8e): 500 feet.

c. Approach altitude AGL (53): 300 feet.

d. Approach velocity true airspeed (52): 500 knots.

5-22

T.O. 1F-4C-34-1-1

Enter the following conditions for the FIRST BOMB
in the mission planning form:

a. Release angle of first bomb (55a), 30’. The re¬
lease angle of the first bomb, the number of bombs
to be released and the release interval will establish
the pattern length. Note that when the release angle
is greater than 45°, the range from pullup to impact
decreases.

b. Low angle release gyro setting (54b): 36.9

c. Release altitude AGL (55c): 1250 feet.

d. Time from pullup to release, tb (55d): 5.55 sec¬
onds.

e. Range from pullup to impact, R 2 4- R 3 (55e):

22, 255 feet.

f. Time from release to impact, t c (55f): 27.20
seconds.

Determine the time required to ripple release the
desired number of bombs (56). Six bombs will re¬
quire 0.70 seconds when released with the interval
selector switch positioned on 0.14 SEC. Multiply the
interval setting by the number of bombs minus one
bomb (N-l).

5 times 0.14 sec. =0.70 second.

The time from pullup to the release of the last bomb
(57a) is the sum of items (56) and (55d).

5.55 sec. + 0.70 sec. = 6.25 sec.

Interpolate the bombing table if necessary for re¬
lease angle that provides a time from pullup to re¬
lease equal to that computed for the last bomb (57a),
using the same release conditions that were used for
the first bomb. Record the following conditions for
the LAST BOMB:

a. Release angle (57b): 35°.

b. Release altitude AGL (57c): 1546 feet.

c. Range from pullup to impact, R 2 to R 3 (57d):

23, 530 feet.

d. Time from release to impact, t c (57c): 30.64
seconds.

The approximate pattern length (58) is equal to the
R 2 + R 3 range of the last bomb, minus the R 2 + R 3
range of the first bomb.

23, 530 ft., minus 22,255 ft. = 1275 ft.

To determine the pullup timer setting, the approxi¬
mate range from pullup to the center of the ripple
pattern (59) must be known: add one-half of the pat¬
tern length to the R 2 + R 3 range of the first bomb
(55e).

22, 255 ft. + (1275 4- 2) = 22, 893 ft.

Note

When the LABS/Target Find mode is used,
item (59) is used to determine the value set
on the WRCS Release Range (Rr) counter.

Refer to item (64) WRCS LABS/TGT Find
Corrections. Complete item (83).

From the target map or photos, select an IP and
measure the IP-to-target distance (60). Determine
the IP-to-pullup distance (61) by subtracting the
pullup-to-center of pattern distance (59), from IP-
to-target distance (60).

29, 000 ft., - 22, 893 ft. = 6107 ft.

The pullup timer setting for no-wind (62) is deter¬
mined by dividing the IP-to-pullup distance (61) by
the approach true airspeed in feet per second (52).

6107 ft. — 844 fps = 7.2 seconds.

Crosswind correction is not required if the crab
angle established during the run-in approach is
maintained in the pullup until final bomb release.

Rangewind correction is applied to the Pullup Timer
and computed as a function of groundspeed. The ef¬
fect is to move the pullup point toward the target for
a headwind and conversely for a tailwind. The cor¬
rection time is added for a headwind and subtracted
for a tailwind. Rangewind correction for the Pullup-
to-Impact (R 2 + R 3 ) range can be obtained from the
loft bombing wind correction table (figure 6-19). En¬
ter the table with the approach TAS (52), the release
angle of the middle bomb, and the rangewind com¬
ponent (26).

Another method to correct R 2 + R 3 is to use the fol¬
lowing equation:

W R (tb + t c ) -r Vgs

where:

Wr = Rangewind Component in feet per sec¬

ond.

tb + t c = Time from pullup to impact of last
bomb.

Vgs = Approach groundspeed in feet per sec¬

ond.

Determine the aircraft groundspeed (63a) in feet per
second: add or subtract the rangewind component
(26) from the approach true airspeed (52). Subtract
for headwind, add for tailwind.

844 fps - 34 fps = 810 fps.

The pullup timer setting corrected for rangewind is
the sum of the R 2 + R 3 wind correction time (63b)
and the groundspeed IP-to-pullup time (63c). Add the
R 2 + R 3 wind correction for headwind, subtract for
tailwind.

+ 1.5 sec. +7.5 sec. = 9.0 sec.

When the WRCS LABS/Target Find mode is used, the
Release Range (Rr) counter setting (64e) is corrected
to include Pullup Timer lead-in time and, if neces¬
sary, R 2 + R 3 wind correction.

The exposure time of the aircraft above a given alti¬
tude may be obtained from the exposure time chart
(figure 6-18).

5-23

T.O. 1F-4C-34-1-1

(F-4C)/F-4D/(F-4E)

Sheet 1 of 7

MISSION PLANNING FORM
NONNUCLEAR

MISSION CONDITIONS

1. Delivery and Release Mode

2. Munition . MU1.CP, (/VHm/. F'yjw eight. $20 _lbs. Drag ^

3. Fuzing:

NOSE

a. Fuze. . Mqotei

b. Arming Delay.(Tolerance ± 2-0/ & sec.). 6/ 7 te—

c. Functioning Delay. .

4. Drag Index and External Weight:

TAIL

a. Outboard: —

b. Inboard: —1

c. Centerline:—-— ,

d. Fuselage: —4

lbs, Drag Index

. lbs, Drag Index .

e. Totals:. T. wgt.

5. Airplane Operating Weight.

6. Fuel Remaining Over Target:

got _ _ lbs, Drag Index f > ^ _

tfio _ lbs, Drag Index ,5V _

p4o _ . f-7 I

ffD _pounds

ytf

pounds

7. Airplane Gross Weight Over Target (Add: #4e, #5, and #6) .... . 1 4Wo

8. TARGET DATA:

a. Altimeter setting over target.

b. Target Elevation MSL.

c. Target Temperature.

d. Target Pressure Altitude.

e. Target Density Altitude (forecast or fig 6- 5 )

Hg.

feet

Sod

feet

9. Approach Course to Target.

10. Minimum Aircraft Recovery Altitude AGL. (Check # 16 minus #19).

(To be established by Major Command)

-Q-4q . “True
N A " — feet

-30 - 20 -10

90 100 110 120 IX 140

°p-l» -120 -110 - 100 - 90 -10 - 70 -00 -SO .. __ ... ..

°C -so - oo -re -to -so -so -30 - 30 -10 o to 30 so to so to

F4.34-V-306-1

Figure 5-8 (Sheet 1 of 4)

5-24

T.O. 1F-4C-34-1-1

(F-4C<@MD^)(F-4E)

MISSION PLANNING FORM
NONNUCLEAR

RELEASE CONDITIONS

Sheet 2 of 7

11. Safe Escape and Fuze Arming:

a. Minimum Release Altitude (AGL) for Frag Clearance. —^-4 - feet

From Safe Escape Table, figure 6-14 or 6-15.

(Ensure that #16 or #28 is greater than #lla)

b. Minimum Release Altitude (AGL) for Fuze Arming. —hLA _ feet

From Fuze Arming Table, figure 6-13, 6-15 or 6-16.

(Ensure that #16 or #28 is greater than #llb)

c. Check Fuze Arm Delay Setting plus Fuze Tolerance, / , \

is LESS THAN Bomb Time of Flight ,.»__.'

d. Impact Velocity of BLU-31/B with FMU-30/B Fuze

(LESS THAN 900 fps). ^- fps

12. Forecast Temperature at Release Altitude MSL

13. Calibrated Airspeed Release Velocity.

14. True Airspeed Release Velocity (Vr).

15. Dive Angle.

16. Release Altitude AGL (Must be greater than #11).

17. Release Altitude MSL (#8b+ #16).

18. Ripple Release Interval (Ir) Setting: . . . (.06) . . . (.10) . .

19. Altitude Lost During Pullout (3.0G) (4.0(5) (5.0G) .

20. Altimeter Lag.SPC OFF_ d/A

°C

knots

A/4

o./4-O

degrees

feet

sec

.._ feet

. .SPC ON A/4 feet

21. Altimeter Position Error Correction(F-4C/D).SPC ON_ Q. _ Afeet

1 Q’Df'’ mPTT -

23. Angle of Attack from zero sight line (fig 6-3)

WIND VALUES

24. Forecast Wind Velocity.

25. Relative Wind Velocity (fig 6-11). .

26. Rangewind Component (head)JteflT .

27. Crosswind Component (left) icigftff.

FPS

10 70

30 40

70 80

,1 1 fl

knots!

350

True.

3/0

— mils

SO_ . knots
knots

34-

— fps . .
-fps . .

knots

170 130 140 ISO 160 170 180 190 600 610 670 630 640 610 660 670 680 690

FPS U.1.1.-1 .X . . I .J , ,,, ,. w, ! . -I- . 1,-L-J-1 ... .1. I , ..

710 770 730 740 710 760 770 780 790

n.|(..| M 1 .J...I...1.,-U-In.

470 430

KNOTS

440

790 800 810 870 830 840 810 860 870 880 890 900 910 970 930 940 910 960 970 980 990 1000 1010 1070 1030 1040 1010 1060

F p $ .i. r Uw.-X YT I_ L-pJ_^_ jL^l_l t j_ i 1 _ Ux^i _ l r L. , j r 4, l - 1 .r 1 —I

KNOTS J ;o 4 |Q 490 100 l!o 170 130 Jo 110 160 170 580 190 600 610 670

F 4-34-V-106-2

Figure 5-8 (Sheet 2 of 4)

5-25

T.O. 1F-4C-34-1-1

(F-4C)/F-4D)/F-4E)

Sheet 4 of 7

MISSION PLANNING FORM
NONNUCLEAR

ROCKET LAUNCH AND GUN FIRING CONDITIONS

Rocket Warhead Used: (MK-1) (MK-5, Heat) (Practice) (M151) (WDU-4A/A)

42. Time of Flight

43. Sight Setting (no wind)

44. Slant Range

45. Horizontal Range

46. Wind Correction

47. Wind Correction

48. Upwind Ainipoint (single poinpdffset)

(Multiply #24 by #46)

49. Relative Wind VecJ

a. Rangewirj(i*^orrection (Multiply #26 by #47)(+H)(-T)

b. Crosa^ind Correction (Multiply #27 x #46)(left)(right)

."True

feet per knot
mils per knot
_feet

. mils
.feet

Setting Corrected for Rangewind (#43 ± #49a) (+H) (-T)

LOFT BOMBING RIPPLE RELEASE CONDITIONS

mils

51. Approach Calibrated Airspeed.

52. Approach True Airspeed (fig 6-4).

53. Approach Altitude AGL.

54. Indicated Approach Altitude MSL (Add; # 8 b, #53, #21)

55. FIRST BOMB (from table):

a. Release Angle of First Bomb.

b. LOW ANGLE Release Gyro Setting (table) ....

c. R elease Altitude AGL.

d. Time from Pullup to Release (t].,).

e. Range from Pullup to Impact (R£ + R 3 ).

f. Time from Release to Impact (t c ).

56. Time Required to Ripple 6Bnmhs at

-497

. knots

1 8-4-f

fps, Soo

knots

300

_ feet

8SO

_ degrees

^egreesj

/-*<?

msec Interval .

(Multiply Interval Setting by number of bombs, minus one bomb).

/ 250

feet

S.SS

seconds

Z2.jzssr feet

2 . 7 . 2.0

seconds

0.70

seconds

F 4-34-V-106-3

Figure 5-8 (Sheet 3 of 4)

5-26

T.O. 1F-4C-34-1-1

(F-4C)^^^

(F-4E)

Sheet 5 of 7

MISSION PLANNING FORM
NONNUCLEAR

57. LAST BOMB;

a. Time from Pullup to Release, t^, (#56+#55d).

b. Release Angle (Obtained from the line that provides #57a).

c. Release Altitude AGL.

d. Range from Pullup to Impact (R 2 + R 3 ).

e. Time from Release to Impact (t c ) (Check #11C).

58. Approx. Pattern Length (#57d minus #55e). . | /jz -rs*

59. Approx. Range from Pullup to Center of Pattern (#55e plus one-half #58) . . . 3

feet

-seconds

. _degrees

. _ / 5 feet

2 - 3.530

~y — — —- feet

30,64

seconds

feet

60. IP-to-Target Distance (from map or photos).

61. IP-to-Pullup Distance (#60 minus #59). . . .

62. Pullup Timer Setting (#61 -j-#52 fps).

63. RANGEWIND CORRECTION;

a. Aircraft ground speed (#52 ±#26).

3-*f.oo o

feet

. ^^^^^^^^^econd^

8/0

b. Rg and R 3 Wind Correction Time (fig 6-19) or.(+H, ^‘

[(#57a + 57e) times (#26, fps)] r#63a.

7.5

c. Ground speed IP-to-Pullup Time (#61 -r #63a).

d. Pullup Timer Setting, Range wind Corrected (#63c ± 63b),
64. WRCS LABS/TGT FIND CORRECTIONS:

fps

seconds

7, O seconds

a. Pullup Timer Lead-in Time desired . . . .
(Minimum Pullup Timer Setting is 0.1 sec.)

| AO

b. Aircraft ground speed (#51 ±#26)

8/0

c. Pullup Timer Setting Converted to Distance
(#64a) times (#64b)

(+)

d. R 2 + R 3 Wind Correction Distance (head^tarrt^.(-H,

8/0

-/2.S3

fps

feet

(#57a + 57e) times (#26fps)

e. Release Range (Rp) Setting
(#59+ # 64c ± 64d)

Haa^gQfeet |

F4-34-V-106-4

Figure 5-8 (Sheet 4 of 4)

5-27

T.O. 1F-4C-34-1-1

TARGET
DENSITY
ALT ALT

_BOMB. GP» 750-LB.<STT7>

< £.0 ^ MILITARY POWER AT PULLUP
GROSS WEIGHT

RELEASE

Sooft

300

500

1 r xJ jo»d-

1 X>

748
841
932
1029
1139
CGgD

1367
i y 1483

1740
1871
1990
2147

C3E>

32
34
* ~36
38
40
42
44
46
, 48

TIME

RELEASE

RANGE

TIME

PULLUP TO

GYRO

PULL-UP

RELEASE

SETTING

TO IMPACT

SEC

DEG

SEC

4.09

26.3

17701

19.41

4.41

28.5

18844

21.09

4.69

30.5

19832

22.66

4.97

32.6

20729

24.19

5.27

34.8

21552

25.73

C5.5S>

<3S^>

<32235}

(77775)

5.83

39.0

22859

28.64

y.y- 6.09

41.1

23335

29.97

& T7S7

43.3

r5 * } <’2T7 24

M, ^~3T73T

6.64

45.5

24005

32.58

6.91

47.6

24180

33.78

7.16

49.7

24235

34.84

7.44

52.1

24205

36.03

7.69

54.3

24074

37.03

_ ^

^-^56.5/^

23854

38.00

Figure 5-9

5-28

T.O. 1F-4C-34-1-1

INFLIGHT CONSIDERATIONS

ERROR SENSITIVITY SUMMARY

DELIVERY ERRORS - Level & Dive Delivery

Release

Parameter

RELEASE

ERROR

HIT “1

SHORT

LONG

Dive Angle

SHALLOW

✓

STEEP

✓

Release Height

HIGH

✓

LOW

;

Airspeed

SLOW

✓

FAST

✓

G-loading
at Release

HIGH

✓

LOW

✓

F4-34-V-107

Figure 5-10

The following is a summary of inflight considerations
that will directly affect the success of the weapons
delivery mission (figure 5-10). The aircrew must be
aware of the least critical and the most critical pa¬
rameters associated with each mode of delivery.
Knowledge of the parameter sensitivity will arm the
aircrew with the information required to evaluate a
delivery situation where, in combat, the delivery
parameters are seldom as planned and may change
for each attack.

AIRSPEED

All weapon data tables are based on true airspeed;
however, the AC should fly calibrated airspeed for
dive deliveries where rapid changes in airspeed,
altitude, and temperature are experienced, since
rapid changes in these parameters cause the air data
computer (ADC) to provide an erroneous true air¬

speed readout. Calibrated airspeed must be corrected
for outside air temperature at the release pressure
altitude to obtain true airspeed. Errors of 30 knots
can exist if these corrections are not made, and/or
the TAS indicator is used for dive deliveries where
rapid changes in temperature and pressure exist.

ANGLE OF ATTACK

Angle of attack error will cause an equal aiming
error; i.e., the line of sight with the pipper, rotates
vertically in proportion to the change in angle of
attack. The aircraft operates within an angle of
attack envelope that is approximately 300 mils. The
parameters that determine the position of the air¬
craft within the envelope must be controlled. These
parameters are included on the angle of attack card:
release true airspeed, dive angle, pressure altitude,
temperature, gross weight, and NORMAL-G-LOAD-
ING. The AC should strive to maintain the normal G
loading for the dive angle. Extreme angle of attack
error will result with a ± one-quarter G-loading er¬
ror at the time of bomb release. The sensitivity of the
remaining angle-of-attack parameters on the weapon
data card can be observed by comparaison. Note the
effect of gross weight is approximately one mil per
1000 pounds of fuel used and bombs released.

DELIVERY MODE

The parameters most sensitive with the dive bomb
delivery are dive angle, release airspeed, and re¬
lease altitude, in that order. Low-level bombing
with fire bombs (napalm) requires an accurate re¬
lease altitude. For strafing, the slant range is all-
important. When firing the 2.75-inch rockets, G-
loading and airspeed must be controlled. Refer to
the error analysis in Section VI for a more accurate
and detailed examination of the various delivery pa¬
rameters .

5-29/(5-30 blank)

T.O. 1F-4C-34-1-1

SECTION VI

TABLE OF CONTENTS

PLANNING CHARTS and TABLES

TITLE

Ballistic Tables
Mission Planning Form
Dive Recovery Charts
Angle of Attack Chart
Airspeed Conversion Chart
Altitude Conversion Chart
Side Ejection Impact Distance
Altimeter Position Error Correction
(F-4C, F-4D)

Altimeter Lag Chart
Sine and Cosine Table
Sight Depression Chart
Relative Wind Vector Chart
Dive Angle vs Distance
Fuze Arming
Safe Escape

Fuze Arming and Safe Escape (Retarded
Bombs)

Fuze Safe Arming Time Required
WRCS Drag Coefficients
Exposure Time Chart (Dive Bombing)
Exposure Time Chart (Loft Bombing)
Loft Bombing Wind Correction
WRCS Ballistic Data (GP Bombs)
(F-4D/E)

Dive Toss Ripple Release
Mk 20 Mod 2 & Mod 3 (Rockeye II)
CBU-24B/B, -29B/B, -49B/B
CBU-52A/B
CBU - 52B/B

CBU - 58/B or CBU - 71/B
M36E2 Incendiary Cluster
BLU-66/B (CBU-46/A) Left Deflection
BLU-45/B (CBU-33/A) Impact Lateral
Displacement

BLU-49/B (CBU-38/A) Impact Lateral
Displacement

BALLISTIC TABLES

PAGE

FIGURE

NO. OF

NO.

SHEETS

6-1

6-4

6-1

6-11

6-2

6-15

6-3

6-16

6-4

6-17

6-5

6-18

6-6

6-20

6-7

6-21

6-8

1/2

6-23

6-9

1/2

6-24

6-10

6-38

6-11

6-39

6-12

6-40

6-13

6-42

6-14

6-44

6-15

6-45

6-16

6-52

6-17

6-56

6-18

6-57

6-18

6-58

6-19

6-59

6-20

6-68

6-21

6 -68D

6-21A

6 -68N

6-21B

6 -68X

6-21C

6 -68AG

6-2 ID

6 -68AR

6-21E

6-69

6-22

6-70

6-23

6-71

6-24

BLU-27/B FIRE BOMB - UNFINNED

The following is an index of tables presented in the
ballistics manuals T.O. 1F-4C-34-1-2 and T.O. 1F-
4C-34-1-2A. Since the change/revision schedules of
these manuals may not coincide, this index may not
reflect the latest ballistic table changes and additions.

PAGE

AGM-45 MISSILE

Level Dive, Loft (See T.O. 1F-4C-
34-1-1A)

BLU- 1C/B FIRE BOMB - FINNED

Level and Dive - Single Release .... 1-1

BLU-1C/B FIRE BOMB - UNFINNED

Level and Dive - Single Release .... 2-1

BLU-27/B FIRE BOMB - FINNED

Level and Dive - Single Release .... 3-1

Level and Dive - Single Release .... 4-1

BLU-31/B Demolition Bomb

Level and Dive - Single Release .... 5-1

(See MLU-10/B & BLU-31/B Impact
Velocity)

BLU-76/B GP BOMB

0° Dive.5A-1

15° Dive.5A-13

30° Dive.5A-25

45° Dive.5A-37

60° Dive.5A-49

BLU-52/B, A/B Chemical BOMBS -
FINNED

Level and Dive - Single Release .... 6-1

CBU-1 A/A DISPENSER AND BOMB

Level and Dive - Single Release .... 7-1

Change 7

6-1

T.O. 1F-4C-34-1-1

PAGE

CBU-2A, A/A, -9/A DISPENSER AND
BOMB

Level and Dive - Single Release .... 8-1

CBU-2B/A DISPENSER AND BOMB

Level and Dive - Single Release .... 9-1
CBU-7A/A DISPENSER AND BOMB . . . . 10-1

CBU-12A, A/A DISPENSER AND BOMB

Level and Dive - Single Release .... 11-1

CBU-24/B, A/B, -29/B, A/B, -49B, A/B,

C/B DISP AND BOMB
Loft Ripple - Eight Bomb Release
(42, 000 lbs GW)

30° (100 msec).12-1

30° (140 msec).12-15

40° (100 msec).12-29

40° (140 msec).12-43

Loft Ripple - Eight Bomb Release
(48, 000 lbs GW)

30° (100 msec).12-57

30° (140 msec).12-71

40° (100 msec).12-85

40° (140 msec).12-99

Level and Dive - Single Release . . . . 12-113

CBU-24B/B, -29B/B, -49B/B, -58/B
DISPENSER AND BOMB
Loft Ripple - Eight Bomb Release
(42, 000 lbs GW)

30° (100 msec).13-1

30° (140 msec).13-15

40° (100 msec).13-29

40° (140 msec).13-43

Loft Ripple - Eight Bomb Release

(48, 000 lbs GW)

30° (100 msec).13-57

30° (140 msec).13-71

40° (100 msec).13-85

40° (140 msec).13-99

Level and Dive - Single Release . . . . 13-113

(DELETE).(14-1)

CBU-30/A DISPENSER AND BOMB

Level - Ripple Release.15-1

CBU-33/A DISPENSER AND MINE

Level and Dive - Single Release .... 15A-1

Level and Dive - Ripple (61 msec) . . . 15A-12

Level and Dive - Ripple (92 msec) . . . 15A-24

Level and Dive - Ripple (140 msec). . . 15A-36

Level and Dive - Ripple (200 msec). . . 15A-48

Level and Dive - Ripple (300 msec). . . 15A-60

CBU-34/A, A/A, -42/A DISPENSER AND
MINE

Level - Ripple Release.

CBU-38A/A DISPENSER AND BOMB

Ripple - (50 msec).

Ripple - (100 msec).

Ripple - (200 msec).

CBU-46/A DISPENSER AND BOMB

Level and Dive - Single Release . . . .
CBU-52A/B DISPENSER AND BOMB

Level and Dive - Single Release . . . .
CBU-52B/B DISP. and BOMB

Level and Dive.

CBU-58/B or CBU-71/B DISP and BOMB

Level and Dive.

CBU-70/B DISP and BOMB

Level and Dive.

16-1

16A-1

16A-17

16A-32

16B-1

16C-1

16D-1

16E-1

16F-1

CTU-l/A RESUPPLY CONTAINER

Container Wt., 250 lbs.17-1

Container Wt., 400 lbs.17-9

Container Wt., 550 lbs.17-17

Container Wt., 700 lbs.17-25

FLARE TABLES (See SUU-25/A,

-25B/A, -42/A Flare Dispenser)

LASER GUIDED BOMB (MK84)

Level and Dive.. 17A-1

Loft Bombing (42, 000 lbs. GW).17A-24

Loft Bombing (48, 000 lbs. GW).17A-38

LASER GUIDED BOMB (M118)

Level and Dive.17B-1

Loft (42, 000 lbs. GW).17B-24

Loft (48, 000 lbs. GW).17B-51

Ml 17 GP BOMB (M131 or MAU-103A/B
FIN)

Level and Dive - Single Release .... 18-1

Dive - Ripple Release.18-42

Loft Bombing - Single Release

(42, 000 lbs GW).18-60

Loft Bombing - Single Release
(48, 000 lbs GW).18-88

M117 (RETARDED) GP BOMB - HIGH
DRAG

Level and Dive - Single Release .... 19-1

Level and Dive - Ripple Release .... 19-21

mi 17 Retarded) gp bomb - low

DRAG

Level and Dive - Single Release .... 20-1

Ml 18 GP BOMB

Level and Dive - Single Release .... 21-1
Loft Bombing - Single Release

(42,000 lbs GW).21-24

Loft Bombing - Single Release

(48, 000 lbs GW).21-51

M129E1 LEAFLET BOMB

Level - Single Release.22-1

M36E2 INCENDIARY CLUSTER BOMB

Level Release.22A-1

Dive Release.22A-12

MC-1 GAS BOMB

Level and Dive - Single Release .... 23-1

MK20 Mod 2 & Mod 3 (ROCKEYE H)

Level and Dive - Single Release

(1.2 thru 8.0 sec).23A-1

Level and Dive - Single Release (by

Hgt).23A-11

(DELETE).(24-1)

MK 82 LDGP BOMB

Level and Dive - Single Release . . . . 25-1

Dive - Ripple Release.25-24

Loft Bombing - Single Release

(42, 000 lbs GW).25-37

Loft Bombing - Single Release

(48, 000 lbs GW).25-65

MK 82 SNAKEYE - HIGH DRAG

Level and Dive - Single Release .... 26-1

Level and Dive - Ripple Release . . . . 26-17

MK 82 SNAKEYE - LOW DRAG

Level and Dive - Single Release .... 27-1

MK 83 LDGP BOMB

Level and Dive - Single Release .... 28-1

Dive - Ripple Release.28-41

6-2

Change 7

T.O. 1F-4C-34-1-1

PAGE

Loft Bombing - Single Release

(42, 000 lbs GW).28-56

Loft Bombing - Single Release

(48, 000 lbs GW).28-84

MK 84 LDGP BOMB

Level and Dive - Single Release .... 29-1
Loft Bombing - Single Release

(42, 000 lbs GW).29-25

Loft Bombing - Single Release

(48, 000 lbs GW).29-53

MLU-10/B & BLU-31/B IMPACT

VELOCITY.30-1

(DELETE).(31-1)

MLU-32/B99 FLARE (BRITEYE)

Level - Single Release.32-1

ROCKETS - 2.75 INCH FFAR

WDU-4A/A Warhead.33-1

MK-1, -5, Practice Warhd.34-1

M-151 Warhd.35-1

(DELETE).(36-1)

(DELETE).(37-1)

GUN PODS AND NOSE GUN

Sight Settings.38-1

(DELETE).(39-1)

(DELETE).(40-1)

(DELETE).(41-1)

SUU-20/A, A/A, B/A BOMB & ROCKET
DISPENSER

BDU-33A/B - Level and Dive.42-1

PAGE

BDU-33A/B - Loft Bombing

(36, 000 lbs GW).42-52

BDU-33A/B - Loft Bombing

(42. 000 lbs GW).42-80

BDU-33/B - Level and Dive.43-1

BDU-33/B - Loft Bombing

(36, 000 lbs GW).43-49

BDU-33/B - Loft Bombing

(42, 000 lbs GW).43-77

MK 106 - Level and Dive.44-1

SUU-21/A BOMB DISPENSER

BDU-33A/B and B/B - Level and Dive . 45-1

BDU-33A/B and B/B - Loft Bombing

(36, 000 lbs GW).45-53

BDU-33A/B and B/B - Loft Bombing

(42, 000 lbs GW).45-81

BDU-33/B - Level and Dive.46-1

BDU-33/B - Loft Bombing

(36, 000 lbs GW).46-51

BDU-33/B - Loft Bombing

(42, 000 lbs GW).46-79

MK 106 - Level and Dive.47-1

SUU-25A/A, B/A, C/A, -42/A FLARE
DISPENSER

MK 24 Flare - Level Release.48-1

LUU-l/B, 5/B Flare - Level Release. . 49-1

LUU-2/B Flare - Level Release .... 50-1

Change 7

6-3

T.O. 1F-4C-34-1-1

(F-4C) (F-4D) (F-4E)

MISSION PLANNING FORM
NONNUCLEAR

MISSION CONDITIONS

1. Delivery and Release Mode-

2. Munition

-Weight.

3. FUZING:

a. Fuze.

b. Arming Delay.(Tolerance*.

c. Functioning Delay (sec.)..

4. Drag Index and External Weight:

a. Outboard: - , -

sec.)

b. Inboard:

c. Centerline:-

d. Fuselage: -

e. Totals:_

5. Airplane Operating Weight . .

6 . Fuel Remaining Over Target:

7. Airplane Gross Weight Over Target (Add: #4e, #5, and #6)

8 . TARGET DATA:

a. Altimeter setting over target.

b. Target Elevation MSL.

c. Target Temperature.

d. Target Pressure Altitude.

e. Target Density Altitude (forecast or fig 6-5)

9. Approach Course to Target.

Sheet 1 of 7

10. Minimum Aircraft Recovery Altitude AGL. (Check #16 minus #19)
(To be established by Major Command)

Op_)30 -120 - 110 100 90 -00 -70 -*0 -SO -40 -30 -» -10 * "

.lbs. Drag.

NOSE

TAIL

,T. wgt. .

. lbs, Drag Index

T. wgt.

lbs. Drag Index

T. wgt.

lbs, Draer Index

T. wgt.

lbs, Drag Index

T. wgt.

lhsJDrag Index

pounds

in. Hg.
. feet
. °C
feet
teet
. “True
. feet

90 100 110 120 130 140

;—130 -i 2 o -iio loo “o w ^^ ^ j- 1 i" ■■T|' | .i. || .T.p. || “|r.‘ | , | ....r.“ | .|.rrf y

F4-34-VI-101-1

6-4

Figure 6-1 (Sheet 1 of 7)

T.O. 1F-4C-34-1-1

(F-4C) (F-4D) (F-4E)

RELEASE CONDITIONS

MISSION PLANNING FORM
NONNUCLEAR

11. Safe Escape and Fuze Arming:

a. Minimum Release Altitude (AGL) for Frag Clearance.
From Safe Escape Table, figure 6-14 or 6-15.
(Ensure that #16 or #28 is greater than #lla)

b. Minimum Release Altitude (AGL) for Fuze Arming . .
From Fuze Arming Table, figure 6-13, 6-15 or 6-16.
(Ensure that #16 or #28 is greater than #llb)

c. Check Fuze Arm Delay Setting plus Fuze Tolerance,

is LESS THAN Bomb Time of Flight ..

d. Impact Velocity of BLU-31/B with FMU-30/B Fuze
(LESS THAN 900 fps) ..

12. Forecast Temperature at Release Altitude MSL

13. Calibrated Airspeed Release Velocity

14. True Airspeed Release Velocity (Vr)

15. Dive Angle

16. Release Altitude AGL (Must be greater than #11)

17. Release Altitude MSL (#8b + #16)

18. Ripple Release Interval (I R ) Setting: . . . (.06) . . . (.10) .

19. Altitude Lost During Pullout (3.0G) (4.0G) (5.0G).

20. Altimeter Lag.SPC OFF.

. (.14)

SPC ON

21 . Altimeter Position Error Correction( F-4C/D).SPC ON

22. Indicated Release Altitude MSL (Add: #17, #20 & #21) . . . .jsP^OFF

23. Angle of Attack from zero sight line (fig 6-3) .

Sheet 2 of 7

SPC ON

degrees

A feet

0 10 20 30 40 SO 60 70 80

WIND VALUES

24. Forecast Wind Velocity . ....

25. Relative Wind Velocity (fig 6-11)

26. Rangewind Component (head) (tail)

27. Crosswind Component (left) (right)

S20 S30 S40 550 560 S70 580 590 600 610 620 630 640 6S0 660 670 680 690 700 710 720 730 740 750

'PS lilll In 11111 .1 111111.I I . I , I.I. .I. I . I I I .I, .1 I. I I .I.I .,,,1 , ,

760 770 780 790 I

. I lilllill llllllllllI IIllll llI!I>1

.0. 1F-4C-34-1-1

(F-4C) (F-4D) (F-4E)

MISSION PLANNING FORM
NONNUCLEAR

DIVE AND LOW LEVEL BOMBING CONDITIONS (SINGLE) (RIPPLE)

* 28. (Ripple Rel) Release Alt of Last Bomb (Must be greater than #11)
From Ripple Table or, #16 minus [ (I R ) (1.69) (V R ) (Sin 9) (N-l)J

29. Bomb Range (not required if ripple table is used).

a. First Bomb (fr. single table).

b. Last Bomb (Interpolate table).

30. Bomb Time of Flight

*a. First Bomb (fr. single or ripple table).

b. Last Bomb (interpolate table).

Sheet 3 of 7

feet

seconds

* 31. Ripple Pattern Length for_bombs from ripple table or,.. feet

P.L. = [(I R ) (1.69) (V R ) (Cos 9) (N-l)] - AR

* 32. Range from First Release to Center of Ripple Pattern.. feet

(fr. ripple table or, #29a plus one-half #31)

* 33. Sight Depression from Flight Path (fr. table or Sight Depression charts)

34. Sight Setting (no wind) (#23 + #33)

*35. Headwind Correction Factor (Add) fr. table .. mil/knot

* 36. Tailwind Correction Factor (Subtract) fr. table.. mil/knot

*37. Crosswind Correction Factor fr. table.. ft/knot

38. Upwind Aimpoint (single point offset)..°True _ feet

(Multiply #24 by #37)

39. Relative Wind Vector:

a. Rangewind Correction.(+H) (-T)_feet, or (+H) (-T) _mils

(Multiply #26 by #35 or #36 and #37)

b. Crosswind Correction.(left) (right) .... _ feet

(Multiply #27 by #37)

40. Sight Setting Corrected for Rangewind (#34 ± #39a).I mils

41. Side Ejection Impact Distance (feet) and Release Sequence (if applicable) fig. 6-6:

* Value can be obtained from Ripple Release Table._ F4-34-vi-un-3

mils

6-6

Figure 6-1 (Sheet 3 of 7)

T.O. 1F-4C-34-1-1

(F-4C)(F-4D)(F-4E)

MISSION PLANNING FORM
NONNUCLEAR

ROCKET LAUNCH AND GUN FIRING CONDITIONS

Rocket Warhead Used: (MK-1) (MK-5, Heat) (Practice) (M151) (WDU-4A/A)

42. Time of Flight.

43. Sight Setting (no wind)

44. Slant Range.

45. Horizontal Range . . .

46. Wind Correction.

47. Wind Correction.

48. Upwind Aimpoint (single point offset) (Multiply #24 by #46) . .

49. Relative Wind Vector:

a. Rangewind Correction iMultiply #26 by #47) (+H) (-T) .

b. Crosswind Correction (Multiple #27 by #46) (left) (right)

50. Sight Setting Corrected for Rangewind (#43 ± #49a) (+H) (-T) .

LOFT BOMBING RIPPLE RELEASE CONDITIONS

51. Approach Calibrated Airspeed.

52. Approach True Airspeed (fig 6-4).

53. Approach Altitude AGL.

54. Indicated Approach Altitude MSL (Add: # 8 b, #21, #53)

55. FIRST BOMB (from table):

a. Release Angle of First Bomb.

b. LOW ANGLE Release Gyro Setting (table).

c. Release Altitude AGL.

d. Time from Pullup to Release (t b ).

e. Range from Pullup to Impact (R 2 + R 3 ).

f. Time from Release to Impact (t c ) (check #llc) . . .

56. Time Required to Ripple_Bombs at

.msec Interval

True

(Multiply Interval Setting by number of bombs, minus one bomb).

fps,

Sheet 4 of 7

seconds

mils

feet

.feet per knot

.mils per knot
_ feet

mils

feet

mils

. knots

knots

. feet
. feet

degrees

. feet
„ seconds
. feet
. seconds
. seconds

F4-34-VI-101-4 |

Figure 6-1 (Sheet 4 of 7)

6-7

T.O. 1F-4C-34-1-1

(F-4C) (F-4D) (F-4E) Sheet 5 of 7

MISSION PLANNING FORM
NONNUCLEAR

57. LAST BOMB:

a. Time from Pullup to Release, t b , (#56 + #55d).. seconds

b. Release Angle (Obtained from the line that provides #57a) .. degrees

c. Release Altitude AGL.. feet

d. Range from Pullup to Impact (R 2 + R 3 ).. feet

e. Time from Release to Impact (t c ) (check #llc).. seconds

58. Approx. Pattern Length (#57d minus #55e).

59. Approx. Range from Pullup to Center of Pattern (#55e plus one-half #58).. feet

60. IP-to-Target Distance (from map or photos).

61. IP-to-Pullup Distance (#60 minus #59).

62. Pullup Timer Setting (#61 4- #52 fps).

63. RANGEWIND CORRECTION:

a. Aircraft ground speed (#52 ± #26).

b. R 2 and R 3 Wind Correction Time (fig 6 - 19 ) or:.

|#57a + #57e) times (#26 fps]]-s- #63a .

c. Ground speed IP-to-Pullup Time (#61 -r #63a).

d. Pullup Timer Setting, Rangewind Corrected (#63c ± 63b)

64. WRCS LABS/TGT FIND CORRECTIONS:

a. Pullup Timer Lead-in Time Desired

(Minimum Pullup Timer Setting is 0.1 sec.).

b. Aircraft ground speed (#52 ± #26).

c. Pullup Timer Setting Converted to Distance

(#64a) times (#64b).

_ feet

..fps

(+H) (-T) _ seconds

d. R 2 + R 3 Wind Correction Distance (head)(tail)

(#57a + #57e) times (#26 fps).

e. Release Range (R R ) Setting

(#59 + #64c ± 64d).

F4-34-VI-101-5

6-8

Figure 6-1 (Sheet 5 of 7)

T.O. 1F-4C-34-1-1

(F-4D) (F-4E)

This form is classified CONFIDENTIAL
when Item #76 or #77 is filled
in for the CBU-24, -29,-49.

MISSION PLANNING FORM
NONNUCLEAR

DIVE TOSS BOMBING (From Dive Toss Bombing Table)

NOTE: Complete sheet 1 and WIND VALUES on sheet 2. When the pickle slant range is 10,000 feet
or greater, Safe Escape and Dive Recovery computations are not required. Check #75 with
#1 lb.

65. Release Calibrated Airspeed

. knots.

66. Release True Airspeed (figure 6-4)

67. Dive Angle of Pickle .

68. Slant Range of Pickle

69. Pullout Acceleration (2.0)(3.0)(4.0)

. degrees.

70. Pickle Altitude AGL

71. Ripple Release Interval (0.06)(0.10)(0.14).

seconds.

72. Time from Pickle to middle bomb release

seconds.

73. Release Altitude AGL of middle bomb

74. Release Angle of middle bomb (+ above, - below horz).

75. Time of fall of middle bomb

. degrees.

seconds.

Determine last bomb time fall
and check #llb is LESS.

* 76. Stick length of (3) (6) (8) (12) bomb ripple.

* 77. Stick length of less than_bomb ripple

(#76 N)times (N-l).

78. (CBU-24, -29) M907 Fuze Setting

seconds.

F4-34-VI-101-6

Figure 6-1 (Sheet 6 of 7)

6-9

T.O. 1F-4C-34-1-1

(F-4D) (F-4E)

Sheet 7 of 7

MISSION PLANNING FORM
NONNUCLEAR

WRCS COUNTER SETTINGS

79. Dive Toss Mode:

a. Drag Coefficient (fig 6-17).

b. Release Advance (#19 x N-l) .

c. Pickle Slant Range (fig 6-17, or #68).

80. Dive Laydown Mode:

a. Release Range (#29a or #32).

b. Release Advance (#19 x N-l)..

81. Laydown Mode:

a. Alt/ RANGE (IP-to-target)..

b. Release Range (#29a or #32).

c. Release Advance (#19 x N-l).

~2~

d. Sight Depression from Level Flight Path

for IP Range to Target (fr. fig 6-10).

82. Offset Bombing or Target Finding Mode:

a. ALT/Range (#8d or IP Pressure Alt.).

b. N-S Target Distance (fr. map).(N) (S)

c. E-W Target Distance (fr. map).(E) (W)

d. (OFFSET BOMB) Release Range (#29a or #32).

e. (OFFSET BOMB) Release Advance (#19 x N-l ).

~T~

83. LABS/TGT Find Mode:

a. ALT./Range (#8d or IP Pressure Alt.) .

b. N-S Target Distance (fr. map).(N) (S)

c. E-W Target Distance (fr. map).(E) (W)

d. Release Range (#64e).

e. Sight Depression from Level Flight Path.

MSEC

.feet

FT x 10
FT x 100

MSEC

J_L

FT x 100

1 1

FT x 10
FT x 100

1 1

MSEC

MILS

1 1

FT x 100

! 1

FT x 100

1 1

FT x 100

1 1

FT x 10
FT x 100

. 1 1

MSEC

1 1

FT x 100

1 1

FT x 100

1 1

FT x 100

1 1

FT x 10
FT x 100

_1 1

MILS

F4-34—VI—101—7

6-10

Figure 6-1 (Sheet 7 of 7)

ALTITUDE LOST DURING PULLOUT - FEET
(1 unit = 100 feet)

T.O. 1F-4C-34-1-1

DIVE RECOVERY CHART

PULLOUT ACCELERATION
3.0 g ATTAINED IN 2.0 SECONDS.
NO SAFETY FACTORS.

NO REACTION TIME

TRUE AIRSPEEDAT START OF PULLOUT - KNOTS
(1 unit * 2 knots)

Figure 6-2 (Sheet 1 of 4)

ALTITUDE LOST DURING PULLOUT

(1 unit a 100 feet)

ISSSSSS!

..:::::

iiBSBBSi

IKKSSKS!

:::::::::::::::

iiiiiiiiiigiiiil

;gig;j!i;!H!i!!!s;

i* 4 *!^^* «sMimaR»B*sa wsai

I«»55? »!

T.O. 1F-4C-34-1-1

6-12

DIVE RECOVERY CHART

400 420 440 460 480 500 520

TRUE AIRSPEED AT START OF PULLOUT - KNOTS
(1 Unit = 2 Knots)

Figure 6-2 (Sheet 2 of 4)

6000

5500

5000

F4-34-VI-102-2

4500

3000 ^ S
=> 1

1500

1000

O 3500
-J ^

£ - 3000

1500

1000

6000

5500

5000

4500

D/VE RECOVERY CHART

KNOTS

WINGS

TAS

LEVEL

450

390

500

460

550

540

600

620

KNOTS

WINGS

TAS

LEVEL

450

1200

500

1440

550

1690

600

1960

KNOTS

WINGS

TAS

LEVEL

450

2390

500

2900

550

3430

600

3960

30°

45°

BANK

2740

3420

3340

4200

3970

5000

4580

5750

ANGLE OF ATTACK

T.O. 1F-4C-34-1-1

IKMriUfiir.1

ZiZSTiZiZWi

KCAS-TRUE MACH NUMBER-KTAS

CALIBRATED AIRSPEED-KNOTS

TRUE AIRSPEED-KNOTS

F4-34-VI-104

Figure 6-4

Change 1

ARGET PRESSURE ALTITUC

T.O. 1F-4C-34-1-1

TARGET PRESSURE ALTITUDE - 1000 FEET

TEMPERATURE - °C

ICAO STANDARD DAY TEMPERATURE - °C

TARGET PRESSURE - INCHES Hg

TARGET DENSITY ALTITUDE

TEMPERATURE - °F

ALTITUDE CONVERSION

ICAO STANDARD DAY PRESSURE and DENSITY ALTITUDE - 1000 FEET

F4-34-V1—121

Figure 6-5

6-17

UNCLASSIFIED

STORE WEIGHT-POUNDS

T.O. 1F-4C-34-1-1

SIDE EJECTION IMPACT DISTANCE

RIGHT OUTBOARD

■ ■1

!a|[|

SS !

STORE WEIGHT-POUNDS

BOTTOM

ALT I MET EH POSITION ERROR CORRECTION Effing

AH CORRECTION - FEET

ALTITUDE

VELOCITY

KCAS

GROSS WT

36,000 LBS

40,000 LBS

45,000 LBS

20,000 FT

25,000 FT

EFFECTIVITY:

(1.) F-4C BEFORE T.O. 1F-4-754.

(2.) F-4D-24 THRU 28 PRIOR TO T.O. 1F-4-754.

SAMPLE:

ASSIGNED ALTITUDE:
AIRSPEED:

GROSS WEIGHT:

1000 FEET
500 KCAS
36,000 POUNDS

FLY:

1000 FEET - 150 FEET, OR 850 FEET
'NDICATED ALTITUDE

• AFTER T.O. 1F-4-754 THE ERROR BECOMES ZERO i ANY
ERROR NOTED DURING ALTIMETER PREFLIGHT.

• FOR F-4E AIRCRAFT, THE ERROR IS ZERO i ANY ERROR
NOTED DURING ALTIMETER PREFLIGHT.

F 4—34-VI —11 9

Figure 6-

6-20

TRUE AIRSPEED - KNOTS

T.O. 1F-4C-34-1-1

ALTIMETER LAG (continued)

•;. v 'w;;,?;::':...I

ALTIMETER LAG - FEET

? F4-34-V -106-2

Figure 6-8 (Sheet 2 of 2)

T.O. 1F-4C-34-1-1

SINE and COSINE TABLE

1.00000

.99985

.99939

.99863

.99756

.99619

.99452

.99255

.99027

.98769

.98481

.98163

.97815

.97437

.97030

.96593

F4-34-VI.107

Figure 6-9

6-23

;ified

SIGHT DEPRESSION

i*B 88 81

\i»m

SIGHT DEPRESSION ANGLE FROM FLIGHT PATH - MILS
(1 Unit ■ 2 Mils)

Figure 6-10 (Sheet 1 of 14)

T.O. 1F-4C-34-1-1

SIGHT DEPRESSION

LEVEL FLIGHT

SIGHT DEPRESSION ANGLE FROM FLIGHT PATH - MILS

(T Unit ^ 2 Mils) F4.34-VI-108-2

Figure 6-10 (Sheet 2 of 14)

RANGE FROM RELEASE TO TARGET - FEET

T.O. 1F-4C-34-1-1

SIGHT DEPRESSION ANGLE FROM FLIGHT PATH - MILS

(1 Unit - 2 Mils) F4-34-VI-108-3

6-26

Figure 6-10 (Sheet 3 of 14)

RANGE FROM RELEASE TO TARGET - FEET
(1 Unit ■ 50 Feet)

T.O. 1F-4C-34-1-1

SIGHT DEPRESSION ANGLE FROM FLIGHT PATH - MILS

(1 Unit = 2 Mils) F4-34-VI-108-5

Figure 6-10 (Sheet 5 of 14)

T.O. 1F-4C-34-1-1

SIGHT DEPRESSION

20° DIVE

Figure 6-10 (Sheet 6 of 14)

6-29

RANGE FROM RELEASE TO TARGET - FEET
(1 Unit = 50 Feet)

T.O. 1F-4C-34-1-1

SIGHT DEPRESSION ANGLE FROM FLIGHT PATH - MILS

(1 Unit = 2 Mils) F4-34-VI-108

Figure 6-10 (Sheet 7 of 14)

6-30

RANGE FROM RELEASE TO TARGET - FEET
(1 Unit = 50 Feet)

T.O. 1F-4C-34-1-1

F4-24-VI-108-8

Figure 6-10 (Sheet 8 of 14)

6-31

T.O. 1F-4C-34-1-1

SIGHT DEPRESSION

40° DIVE

F4-34-VI-108-10

Figure 6-10 (Sheet 10 of 14)

RANGE FROM RELEASE TO TARGET - FEET
(1 Unit = 50 Feet)

T.O.* 1F-4C-34-1-1

8000

7000

6000

5000

4000

3000

2000

SIGHT DEPRESSION ANGLE FROM FLIGHT PATH - MILS
(1 Unit = 2 Mils)

F 4-34-VI-108-1 2

Figure 6-10 (Sheet 12 of 14)

6-35

RANGE FROM RELEASE TO TARGET - FEET
(1 Unit = 50 Feet)

T.O. 1F-4C-34-1-1

SIGHT DEPRESSION ANGLE FROM FLIGHT PATH - MILS
(1 Unit = 2 Mils)

F4-34-VI-108

6-36

Figure 6-10 (Sheet 13 of 14)

RANGE FROM RELEASE TO TARGET - FEET
(1 Unit = 50 Feet)

T.O. 1F-4C-34-1-1

SIGHT DEPRESSION ANGLE FROM FLIGHT PATH - MILS
(1 Uni* = 2 Mils)

F4-34-VI-108-14

Figure 6-10 (Sheet 14 of 14)

6-37

T.O. 1F-4C-34-1-1

LEFT CROSSWIND (-)

RIGHT CROSSWIND (+)

EXAMPLE #1: • TAI

GIVEN:

a. WIND DIRECTION. 350° *

b. APPROACH COURSE . .-040° A

FIND: RELATIVE WIND.3T0 6

EXAMPLE #2:

GIVEN:

a. WIND DIRECTION.040

b. APPROACH COURSE . . 350
(Since 350° is greater then 040°,

add 360° to the wind direction.)

c. WIND DIRECTION. 400°

b. APPROACH COURSE.. .- 350°

FIND: RELATIVE WIND. 050°

60°

1 _

200 °" T "~—f -1

190°

h—r-M

Tt ■ *

F4-34-VU109

RELATIVE WIND VECTOR CHART

Figure 6-11

UNCLASSIFIED

ALTITUDE ABOVE TARGET- 1000 FEET
(1 unit = 200 feet)

VIVE ANGLE VS DISTANCE

(1 unit ~ 200 (e*t)

DISTANCE FROM TARGET- 1000 FEET

F4-34-VI-110

Figure 6-12

6-39

T.O. 1F-4C-34-1-1

FUZE ARMING

MINIMUM RELEASE ALTITUDE OR VERTICAL DROP
REQUIRED FOR

GENERAL PURPOSE, LOW DRAG, BOMB FUZE ARMING

RELEASE

M904

M905

FMU-72/B

FMU-26A/B, -26B/B

NOSE OR TAIL FUZE

ARMING DELAY

SETTING

TAS

KTS

DIVE

ANGLE

DEG

M 9 0 4

M 9 0 5

4 SEC

6 SEC

4 SEC

6 SEC

360

370

830

290

630

360

1170

2020

950

1590

360

1410

2380

1170

1910

360

1640

2720

1370

2210

360

1860

3050

1570

2500

360

2070

3360

1760

2770

360

2270

3650

1940

3030

360

2450

3930

2100

3270

360

2620

4170

2250

3490

360

2730

4350

2390

3690

360

2870

4550

2510

3860

400

370

830

290

630

400

1250

2140

1020

1700

400

1520

2540

1260

2050

400

1780

2920

1490

2380

400

2020

3280

1710

2700

400

2250

3630

1920

3010

400

2470

3960

2120

3290

400

2670

4260

2300

3560

400

2860

4530

2470

3800

400

2990

4730

2620

4020

400

3140

4950

2750

4220

440

370

830

290

620

440

1340

2260

1100

1810

440

1630

2700

1360

2180

440

1910

3120

1610

2550

440

2180

3520

1850

2900

440

2430

3900

2080

3240

440

2670

4250

2300

3550

440

2900

4590

2500

3850

440

3100

4890

2680

4110

440

3250

5140

2850

4360

440

3410

5360

2990

4570

480

370

830

290

620

480

1420

2380

1170

1910

480

1730

2860

1450

2320

480

2040

3310

1730

2720

480

2340

3750

1990

3110

480

2610

4160

2240

3470

480

2880

4550

2480

3810

480

3120

4910

2710

4130

480

3340

5240

2890

4430

480

3510

5490

3070

4690

480

3690

5750

3230

4920

520

370

820

290

620

520

1500

2500

1240

2010

520

1840

3010

1550

2460

520

2170

3510

1850

2900

520

2500

3980

2130

3310

520

2790

4430

2400

3700

520

3080

4850

2650

4160

520

3340

5230

2890

4420

520

3580

5590

3110

4730

520

3760

5860

3300

5010

520

3960

6140

3470

5260

4C—34—1-1—(186—II

6-40

Change 8

Figure 6-13. (Sheet 1 of 3)

T.O. 1F-4C-34-1-1

FUZE ARMING

E >>

(CONTINUED)

■

MINIMUM RELEASE ALTITUDE OR VERTICAL DROP
REQUIRED FOR

GENERAL PURPOSE, LOW DRAG, BOMB FUZE ARMING

RELEASE

M 9 0 4

M 9 0 5

M904

M905

FMU-72/B

FMU—26A/B, -26B/B

NOSE OR TAIL FUZE

ARMING DELAY

SETTING

TAS

KTS

DIVE

ANGLE

DEG

4 SEC

6 SEC

4 SEC

6 SEC

560

370

820

290

620

560

1580

2610

1310

2110

560

1940

3160

1640

2590

560

2300

3690

1960

3050

560

2640

4190

2260

3500

560

2960

4670

2550

3920

560

3270

5110

2830

4310

560

3550

5520

3080

4680

560

3810

5900

3310

5010

560

4000

6190

3520

5310

560

4210

6490

3700

5580

600

370

820

290

620

600

1590

2630

1380

2200

600

1980

3200

1730

2700

600

2360

3760

2060

3190

600

2730

4290

2390

3660

600

3070

4800

2690

4100

600

3390

5270

2980

4510

600

3690

5700

3250

4900

600

3970

6100

3490

5250

600

4210

6460

3710

5560

600

4430

6770

3900

5840

4C-34-1-1-1186-2)

Figure 6-13. (Sheet 2 of 3)

Change 8

6-40 A/ (6-40Bblank)

T.O 1F-4C-34-1-1

run ARMING

(CONTINUED)

IliiPPli

CBU-24B/B OR CBU-58/B

MINIMUM RELEASE ALTITUDE FOR FUZE ARMING

HOB - 1800 FEET
ARMING TIME - 3.0 SECONDS

RELEASE

DIVE

ANGLE

MINIMUM RELEASE ALTITUDES

DEG

400 KTAS

440 KTAS

480 KTAS

520 KTAS

560 KTAS

600 KTAS

2020

2630

2690

2750

2800

2850

2910

3190

3300

3420

3530

3650

3750

3670

3830

3990

4150

4310

4450

These minimum release altitudes
are based on an 1800 ft Height-of
the minimum release altitudes foi
add the difference between the pla
the values listed in the table.

for a 3-second arming time
-Burst (HOB). To determine
r other HOB's, algebraically
inned HOB and 1800 ft to

4C—34-1—1—1186—31

Figure 6-13. (Sheet 3 of 3)

Change 8

6-41

T.O. 1F-4C-34-1-1

SAFE ESCAPE

REQUIRED FOR SAFE

MINIMUM
SEPARATION

DIVE DELIVERY-LOW DRAG

RELEASE ALTITUDE*

AND GROUND CLEARANCE DURING RECOVERY

RELEASE

ALTITUDE LOST
0URINGPULL0UT

TSS

KTS

DIVE ANGLE
DEG

360

150

280

430

610

820

1050

360

1300

360

1580

360

1880

360

2200

360

2550

400

170

400

330

400

510

400

730

400

980

400

1270

400

1580

400

1930

400

2310

400

2720

400

3150

440

200

440

380

440

600

440

860

440

1160

440

1500

440

1880

440

2300

440

2760

440

3250

440

3770

480

230

480

430

480

690

480

990

480

1340

480

1750

480

2200

480

2700

480

3240

480

3820

480

4440

520

260

520

490

520

780

520

1130

520

1540

520

2010

520

2530

520

3110

520

3740

520

4420

520

5140

560

290

560

550

560

880

560

1280

560

1750

560

2280

560

2880

560

3540

560

4250

560

5010

560

5810

600

320

600

620

600

990

600

1440

600

1960

600

2560

600

3230

600

3960

600

4730

600

5560

600

6410

MINIMUM REL ALT FOR FRAGMENTATION ENVELOPE CLEARANCE (FEET)

M118 BOMB

M117 BOMB

MK 84 BOMB

MK 83 BOMB

MK 82 BOMB

BLU-31/B
LAND MINE

1100

1000

1200

1000

900

1000

1300

1200

1400

1200

1000

1200

1500

1700

1500

1300

1400

1800

1700

1900

1700

1500

1600

2000

1900

2200

1900

1700

1900

2200

2100

2400

2100

1900

2000

2400

2300

2600

2300

2100

2200

2600

2500

2800

2500

2200

2400

2700

26 00

2900

26 00

2400

2500

2900

2800

3100

2800

2500

2700

3000

2900

3200

29 0 0

2600

2800

1100

1000

1200

1000

900

1300

1200

1400

1200

1100

1200

1600

1500

1700

1500

1300

1400

1800

1700

2000

1700

1500

1700

2100

1900

2200

2000

1800

1900

2300

2200

2500

2200

1900

2100

2500

2400

2700

2400

2200

2300

2700

2600

2900

26 00

2300

2400

2900

2700

3100

2800

2500

3100

2900

3300

2900

2800

28 00

3200

3400

3200

1100

1000

1200

1000

900

1400

1200

1 500

1300

1100

1200

1600

1500

1800

1500

1400

1900

1800

2100

1800

1500

1600

2200

2000

2300

2100

1900

1800

2400

2300

2600

2300

1900

2000

2600

2400

2800

2500

2300

2200

29 00

2700

3100

2800

2300

2400

3100

2800

3300

29 0 0

28 00

2800

3300

3400

3300

3800

38 00

3800

1100

1000

1200

1000

900

1400

1200

1500

1300

1200

1100

1700

1500

1800

1600

1400

2000

1800

2100

1900

1500

1600

2300

2000

2400

2100

1900

2500

2300

2700

2400

2000

2100

2800

2400

3000

2600

2400

2300

3000

2700

3200

2900

2700

3300

3400

3300

3900

4500

1100

900

1200

1000

900

1400

1200

1500

1300

1200

1800

1500

1900

1600

1500

1400

2100

1800

2200

2000

1600

1700

2400

2000

2500

2200

2000

2700

2300

2800

2500

2100

2200

2900

26 00

3100

27 00

2600

3200

3300

3200

3800

38 00

3800

4500

5200

1100

900

1200

1000

900

1500

1200

1600

1300

1200

1800

1500

1900

1700

1500

2100

1800

2300

2000

1700

2400

2000

2600

2200

2100

2000

2700

2300

2900

2600

2300

3000

2900

3200

2900

36 00

3600

36 00

3600

36 00

4300

5100

5900

1100

900

1200

1000

900

1500

1200

1600

1300

1200

1800

1500

200 0

1700

1600

1500

2100

1900

2400

2000

1700

2500

2100

2700

2300

2200

2000

2800

26 00

3100

2600

26 0 0

2600

3300

3400

3300

4000

48 00

4800

48 00

48 0 0

56 00

5600

56 00

56 0 0

5600

560 0

6500

■X. THESE MINIMUM RELEASE ALTITUDES ARE BASED ON A 4.0G RECOVERY
AND ASSUME THAT THE 4.00 IS ATTAINED WITHIN 2.0 SEC AFTER
RELEASE.

Note THE AIRCREW MUST DETERMINE THE MINIMUM RELEASE ALTITUDE THAT
WILL PROVIDE THE REQUIRED GROUND CLEARANCE.

F4-34-VI-112-1

Figure 6-14 (Sheet 1 of 2)

6-42

,' U-S. GOVERNMENT PRINTING OFFICE: 1972-769 672/5141

SAFE ESCAPE (continued)

T.O. 1F-4C-34-1-1

LEVEL DELIVERY-LOW DRAG

MINIMUM RELEASE ALTITUDES
FOR SAFE SEPARATION (LEVEL RELEASE)

4.0 G MIL POWER PULLUP *

RELEASE

TAS

KNOTS

MINIMUM REL ALT FOR

FRAGMENTATION ENVELOPE CLEARANCE (FEET)

M118

BOMB

MK 84
BOMB

MK 83
BOMB

m in

BOMB

MK 82
BOMB

BLU-31/B

LANDMINE

360

500

600

500

400

500

400

500

600

400

440

500

400

300

480

400

500

400

300

520

400

500

400

300

560

400

500

300

400

300

600

400

500

300

400

300

360

1400

1700

1300

1200

1100

900

400

1300

1600

1200

1100

1000

800

440

1200

1500

1100

900

700

480

1100

1400

1000

800

500

520

1000

1400

900

400

560

1000

1300

800

900

400

600

900

1200

600

800

700

400

* THESE MINIMUM RELEASE ALTITUDES ASSUME THAT A 4.0G MIL POWER IS ATTAINED 2.0 SECONDS AFTER RELEASE. THE G IS MAINTAINED UNTIL
A 20 DEG - 30 DEG CLIMB OUT ANGLE IS ATTAINED. AN ALTERNATE MANEUVER MAY BE ACCOMPLISHED BY PERFORMING A 4.0-G BANKED TURN
USING A 60° BANK ANGLE. THIS COMBINATION OF G FORCES AND BANK ANGLE WILL PRODUCE A CLIMBING TURN-NOT A LEVEL TURN.

2.75 INCH FFAR

MINIMUM LAUNCH ALTITUDES

REQUIRED FOR SAFE RECOVERY FROM FRAGMENTS

2.75 FFAR W/MK 1 WARHEAD

4.0 G RECOVERY

TO 10 DEG CLIMB

RELEASE

Sr^gStl

K TAS

360

600

900

1100

1300

1500

2100

2400

380

600

900

1100

1400

1600

2300

2700

400

700

900

1100

1400

1600

2300

3000

420

700

900

1200

1500

1700

2300

3300

440

700

1000

1300

1500

1800

2400

3700

460

700

1000

1400

1600

1900

2500

4000

480

700

1100

1400

1700

2000

2700

4 4 0 0

500

800

1100

1400

1700

2 0 0 0

2900

4 700

520

800

1100

1400

1800

2 2 0 0

3200

5100

540

900

1200

1500

1900

2 4 0 0

34 00

5500

560

900

1200

1500

1900

2 4 0 0

3600

5800

2.75 FFAR W/M 151 WARHEAD

4.0 G RECOVER TO 10 DEG CLIMB

RELEASE

KT AS

360

500

700

900

1100

1300

1900

2 4 00

380

500

800

1000

1200

1400

2000

2700

400

600

800

1000

1300

1500

2 000

3 000

420

600

800

1100

1300

1500

2 2 0 0

3300

440

600

900

1100

1400

1600

2300

3700

460

700

900

1200

1400

1700

2 500

4 000

480

700

1000

1200

1500

1700

2700

4 4 00

500

700

1000

1300

1500

1800

2900

4 7 00

520

700

1000

1300

1600

1900

3200

5100

540

800

1100

1400

1600

2000

3500

5500

560

800

1100

1400

1700

2100

3700

5800

Figure 6-14 (Sheet 2 of 2)

6-43

T.O. 1F-4C-34-1-1

* These minimum release altitudes are based on 4.0G recovery and assume that the 4 ,0G is attained within
2.0 Sec after release. The aircrew must determine the minimum release altitude that will provide the re¬
quired ground clearance.

**For the 20° and 30° dive release conditions listed, the bomb time of flight is

fuze arming for the M904 fuze with a 2.0 Sec., arming delay setting and the FMU-54/B fuze with a 2.5

Sec ., arming delay setting.

Figure 6-15

UNCLASSIFIED

T.O. 1F-4C-34-1-1

FUZE SAFE ARMING TIME REQUIRED

LOW ALTITUDE LEVEL RELEASE - LEVEL,
CONSTANT SPEED ESCAPE MANEUVER

SAFE

VERTICAL DROP

ARMING

TIME

FUZE ARMING

SEC

FEET

AIRCRAFT TO BOMB
SLANT RANGE DISTANCE
AT FUZE ARMING
FEET

M117, MK—81, MK-82

1000

800

810

600

630

MK-83

1200

900

910

600

610

MK-84

1600

1400

1410

1200

1210

M118

1300

1100

1110

900

910

The values listed are applicable for use with single, pairs, salvo, or timed
ripple releases. A straight and level, constant-speed, escape maneuver is
assumed after release .

AIRCRAFT
POSITION AT
FUZE ARMING

RELEASE-

VERTICAL DROP

FUZE ARMING

.F4-34-IV-107

Figure 6-16 (Sheet 1 of 7)

T.O. 1F-4C-34-1-1

FUZE SAFE ARMING TIME REQUIRED

LOW ALTITUDE LEVEL RELEASE-4.0 G PULLUP
OR 4.0 G-60° BANKED TURN ESCAPE MANEUVER.

REL

SAFE

VERTICAL DROP

AIRCRAFT TO BOMB

ARMING

SLANT RANGE DISTANCE

TIME

FUZE ARMING

AT FUZE ARMING

KTAS

SEC

FEET

MU7, MK-81, MK-82

400

4.8

400

1080

500

4.2

300

800

600

4.2

300

800

MK-83

400

4.9

400

1090

500

4.4

350

900

600

4.2

300

800

MK-84

400

5.7

600

1540

500

5.2

500

1320

600

5.2

500

1330

M118

400

5.3

500

1300

500

4.7

400

1050

600

4.7

400

1050

Note

The values listed are applicable
releases only and assume that the
neuver acceleration within two s
level ripple release is to be acco
straight and level throughout the
safe arming times listed for a lev
maneuver should be used and min
ingly.

: or use
air era
econds
mpl ish<
entire
el relec
imum r

with singles, pairs, or salvo type
: t attains the 4.0 G escape mo-
after release. If a low altitude
:d where the aircraft is held
ripple release time cycle, the
jse - level constant speed escape
elease altitudes selected accord-

Figure 6-16 (Sheet 2 of 7)

6-46

T.O. 1F-4C-34-1-1

LOW TO MEDIUM ALTITUDE DIVE RELEASE - 4 0 G
PULLUP TO 20°- 30°CLIMB ESCAPE MANEUVER

RELEASE

SAFE

VERTICAL

AIRCRAFT TO BOMB

TAS

DIVE

ARMING

DROP TO

SLANT RANGE DISTANCE

ANGLE

TIME

FUZE ARMING

AT FUZE ARMING

KTS

DEG

SEC

FEET

MU7, MK—81, MK-82

400

4.7

1200

1050

4.7

1900

1030

4.7

2600

990

500

4.2

1200

790

4.2

2000

760

4.2

2800

740

600

3.8

1200

620

3.8

2100

610

3.8

2950

630

MK-83

400

4.8

1250

1100

4.8

2000

1080

4.7

2600

990

500

4.5

1300

920

4.5

2200

910

4.5

3000

890

600

4.1

1400

810

4.1

2300

730

4.1

3200

750

V' • ,

MK-84

400

5.2

1400

1340

5.1

2200

1280

5.1

2900

1260

500

4.9

1500

1170

4.9

2500

1160

4.7

3200

1060

600

4.6

1600

1030

4.6

2700

1010

4.6

3700

1040

MU8

400

5.0

1300

1190

5.0

2100

1180

4.9

2700

1100

500

4.7

1400

1040

4.7

2300

1030

i /

4.7

3100

1020

600

4.5

1500

930

4.4

2500

870

4.4

3500

890

Note

The values listed are applicabh
type releases only and assume t
cape maneuver acceleration wi
timed ripple releases, where th
flight condition until the last b
should be increased by an amou
cycle.

for us
rat the
thin tw
e aircrc
omb is
nt equc

s with singles, pairs or salvo
aircraft attains the 4.0 G es-
d seconds after release. For
ift remains in a fixed dive angle
released, the safe arming time
il to the ripple release time

Figure 6-16 (Sheet 3 of 7)

6-47

T.O. 1F-4C-34-1-1

RELEASE

SAFE

VERTICAL

AIRCRAFT TO BOMB

SLANT RANGE DISTANCE

ALTITUDE

ABOVE TARGET
FEET

TAS

KTS

arming

DROP TO

TIME

SEC

FUZE ARMING
FEET

AT FUZE ARMING

FEET

M117, MK-

81.

MK-82

400

1060

1070

10,000 OR

500

820

830

LOWER

600

630

400

1980

1990

20,000

500

1340

1350

600

1050

1090

400

2780

30,000

500

1980

1990

600

1640

1680

MK-

-83

10,000 OR

400

1340

500

1060

LOWER

600

830

850

400

2360

20,000

500

1980

600

1630

1650

400

3190

30,000

500

2760

600

2330

2350

MK-

-84

10,000 OR

LOWER

400

500

600

1740

1430

1420

1740

1430

400

2890

20,000

500

2470

600

2080

2090

400

3810

30,000

500

3330

600

2860

2870

MU8

10,000 OR

400

1400

500

1100

1110

LOWER

600

1110

1120

400

2440

20,000

500

2060

600

1690

1720

400

3290

30,000

500

2840

2850

600

2390

2430

| Note |

The lower air density at high altitudes is responsible for the increase in required safe arming time for high alti
tude releases. A linear interpolation between the safe arming time values listed for 10,000, 20,000, and
30,000 feet may be accomplished to determine the required safe arming time value for intermediate altitudes.

6-48

UNCLASSIFIED

T.O. 1F-4C-34-1-1

FUZE SAFE ARMING TIME REQUIRED

HIGH ALTITUDE LEVEL RELEASE
2.0 G PULLUP - MILITARY POWER

RELEASE

SAFE

VERTICAL

AIRCRAFT TO BOMB

ALTITUDE

ABOVE TARGET
FEET

TAS

KTS

ARMING

DROP TO

SLANT RANGE DISTANCE

TIME

SEC

FUZE ARMING

FEET

AT FUZE ARMING

FEET

Mill, NIK-

-81

NIK-82

10,000 OR

LOWER

609

1020

■9

608

603

1022

1020

1066

1845

20,000

821

1403

Wi.

811

1394

400

1990

3059

30,000

500

1341

2357

600

1048

1824

MK-

10,000 OR

400

818

1403

500

605

1016

LOWER

600

602

1011

400

1338

2350

20,000

500

817

1399

600

812

1390

400

1986

3061

30,000

500

1645

2930

600

1326

2344

NIK-84

10,000 OR

LOWER

400

888

1473

500

600

887

885

1474

1467

400

3012

20,000

500

2452

600

2444

wmm

4346

30,000

I ' 1 'PH

3674

600

3021

M118

10,000 OR

LOWER

866

1451

: 1RB

865

860

1453

1444

400

2412

20,000

500

1904

600

---■ .H9P 1

1888

400

2062

3136

30,000

500

2059

3636

600

1688

2965

| Notes |

• The lower air density at high altitudes is responsible for the increase in required safe arming time for high altitude releases. A linear interpolation

between the safe arming time values listed for 10,000, 20,000, and 30,000 feet may be accomplished to determine the required safe arming time
value for intermediate altitudes. /?

F4-34-IV-110-2

Figure 6-16 (Sheet 5 of 7)

6-49

UNCLASSIFIED

FUZE SAFE ARMING TIME REQUIRED

HIGH ALTITUDE LEVEL RELEASE
3.0 G PULLUP - MILITARY POWER

RELEASE

SAFE

VERTICAL

AIRCRAFT TO BOMB

ALTITUDE

ARMING

DROP TO

SLANT RANGE DISTANCE

TAS

TIME

FUZE ARMING

AT FUZE ARMING

ABOVE TARGET
FEET

KTS

SEC

FEET

Mill, MK-

-81, MK-82

609

1389

528

949

425

947

I WTTWM

1066

2237

609

1407

603

1400

400

1990

3296

30,000

500

1341

2731 ‘

600

810

1899

MK-

-83

10,000 OR

LOWER

60S

605

423

1387

1409

943

1062

2239

817

1946

602

1404

400

3301

30,000

500

2734

600

2 529

MK-84

10,000 OR

400

888

1962

500

665

1469

LOWER

600

664

1469

1429

2895

20,000

1142

2627

885

2035

400

2479

3989

30,000

500

3476

600

3301

M118

10,000 OR

LOWER

400

500

600

866

646

643

1939

1450

1446

400

1118

2293

20,000

500

866

1994

600

858

2000

400

3375

500

3442

600

3243

I Notes I

• The lower air density at high altitudes is responsible for the increase in required safe arming time for high altitude releases. A linear interpolation
between the safe arming time values listed for 10,000, 20,000, and 30,000 feet may be accomplished to determine the required safe arming time

F4-34-IV-110-3

Figure 6-16 (Sheet 6 of 7)

UNCLASSIFIED

T.O. 1F-4C-34-1-1

FUZE SAFE ARMING TIME REQUIRED

HIGH ALTITUDE LEVEL RELEASE
4.0 G PULLUP - MILITARY POWER

RELEASE

ALTITUDE

TAS

ABOVE TARGET
FEET

KTS

10,000 OR
LOWER

SAFE

VERTICAL

AIRCRAFT TO BOMB

ARMING

DROP TO

SLANT RANGE DISTANCE

TIME

FUZE ARMING

AT FUZE ARMING

SEC

FEET

Min, MK-81, MK-82

10,000 OR

400

500

600

LOWER

400

20,000

500

600

400

30,000

500

600

10,000 OR

400

500

600

LOWER

400

20,000

500

600

400

30,000

500

600

Notes

•The values listed are applicable for use with singles, pairs, or salvo type releases only and assume that the aircraft attains the pre-planned escape
maneuver pullup acceleration within two seconds after release. For timed ripple releases, where the aircraft remains in a straight and level flight
path condition until the last bomb is released, the safe arming time should be increased by an amount equal to the ripple release time cycle.
eThe lower air density at high altitudes is responsible for the increase in required safe arming time for high oltitude releases. A linear interpolation
between the safe arming time values listed for 10,000, 20,000, and 30,000 feet may be accomplished to determine the required safe arming time value
for intermediate altitudes.

Figure 6-16 (Sheet 7 of 7)

6-51

UNCLASSIFIED

T.O. 1F-4C-34-1-1

WRCS DRAG COEFFICIENTS

FOR ALL BOMBS V e = 0 <ps (0 volts)

DIVE

RELEASE

5000

PICKLE SLANT RANGE (FEET)

ANGLE

TAS

AND

BOMB

DEG

KTS

BELOW

7500

10,000

15,000

20,000

M 117 GP

400

1.00

1.02

1.03

1.05

1.07

500

1.01

1.02

1.03

1.05

1.08

600

1.02

1 04

1.06

1.10

1.15

400

1.00

1.01

1.02

1.04

1.06

500

1.00

1.01

1.02

1.05

1 08

600

1.02

1.04

1.07

1.12

1.17

400

1.00

1.01

1.02

1 04

1.06

500

1.00

1.01

1.02

1.05

1.09

600

1.02

1.05

1.08

1.14

1.22

400

1.00

1.02

1.03

1.05

1.07

500

1.01

1.02

1.03

1.07

1.10

600

1.01

1.05

1.09

1.16

1.23

M 117/MAU-91

400

1.19

1.17

1.18

1.21

(LOW DRAG)

500

600

1.23

1.27

1.20

1.24

1.19

1.20

1.26

1.23

1.31

400

1.23

1.20

1.19

1.21

1.23

500

1.26

1.22

1.21

1.22

1.26

600

1.31

1.27

1.30

1.36

400

1.24

1.23

1.25

500

i*v

1.27

1.25

1 26

1.29

600

1.33

1.37

1.43

400

1.45

1.38

1.35

1.34

500

1 49

1.40

1 36

1.36

600

1.54

1.45

1.43

1.47

1.50

MK 82 LDGP

400

1.00

1.02

1.03

1.05

1.07

500

1.02

1.03

1.05

1.07

600

1.03

1.04

1 06

1.09

1.13

400

1.01

1.02

1.03

1.05

1.06

500

1.01

1.02

1.03

1.05

1.08

600

1.03

1.04

1.06

1.10

1.14

1.01

1 02

1.03

1.04

1.06

500

1.01

1.02

1.03

1.06

1.09

600

1.03

1.05

1.07

1.11

1.16

400

1.03

1.04

1.05

1.06

1.08

500

1 04

1.04

1.05

1.08

1.11

600

1.03

1.05

1.08

1.13

1.19

MK 82

400

1.03

1 05

1.07

1.10

1.14

SNAKEYE 1
(LOW DRAG)

500

600

1.03

1.05

1.08

1.07

1.11

1.17

1.15

1.23

400

1.03

1.05

1.06

1.10

1.14

500

1.03

1.04

1.06

1.10

1.14

600

1.05

1.08

1.11

1.18

1.22

400

1.03

1.04

1.06

1.09

1.12

500

1.03

1.04

1.06

1.11

1.14

600

1.06

1.09

1.12

1.20

1.18

400

1.05

1.06

1.08

1.11

1.14

500

1.05

1.07

1.08

1.13

1.18

600

1.06

1.10

1.14

1.22

1.30

MK 83

400

1.00

1.02

LDGP

500

1.00

1.01

1.02

1.04

600

1.00

1.01

1.03

1.05

400

1.00

1.01

1.03

500

1.00

1.01

1.04

600

1.00

1.03

1.05

400

1.00

1.01

1.02

500

1.00

1 00

1.00

1.01

1.03

600

1.00

, 1.00

1.04

1.07

400

1 00

1.00

1:00

1.02

500

1.00

1.02

1.00

1.02

1.03

600

1.00

1.04

1.07

MK 84

400

1.08

1.06

LDGP

500

1.10

1.08

1.07

1.06

1.07

600

1.12

1.09

1.08

1.09

400

1.10

1.08

1.07

500

1.11

1.08

1.07

1.08

600

1.14

1.10

1.09

1.10

400

1.14

1.11

1.10

1.09

500

1.16

1.12

1.10

1.09

1.10

600

1.18

1.14

1.12

1.13

400

1.24

1.19

1.17

1.15

1.16

500

1.26

1.20

1.17

1.15

1.17

600

1.26

1.21

1.18

1.17

F 4 - 34 - VI — 114—1

Figure 6-17 (Sheet 1 of 4)

6-52

T.O. 1F-4C-34-1-1

: : ■■ . MM ■

WRCS DRAG COEFFICIENTS (continued)

FOR ALL BOMBS V e = 0 fps (0 Volts)

DIVE

RELEASE

5000

PICKLE SLANT RANGE (FEET)

AND

BOMB

DEG

KTS

BELOW

7500

10,000

15,000

20,000

MK 84

400

1.08

1.07

1 07

1.07

1.08

LASER

500

600

1.11

1.13

1.09

1.11

1.09

1.11

1.07

1.11

1.09

1.14

400

1.10

1.09

1.08

500

1 11

1.09

1.08

1.09

1.10

600

1.13

1.12

1.11

1.13

1.15

400

1.15

1.12

1.11

1.12

500

l.U

1.13

1.12

111

1.14

600

1.22

1.16

1.15

1.16

1.17

400

1.24

1.20

119

1.18

1.20

500

1.26

1.21

1.18

1.21

600

1.25

1.23

1.21

1.23

M 118 GP

400

1.05

1.06

500

1 07

1.06

1.05

1.03

1.07

600

1.09

1.08

1.10

1.12

400

1.07

1.06

1 06

1.05

1.07

500

1 07

1 06

1.05

1 06

1 08

600

1.10

1.09

1.11

1.14

400

1 09

1 07

1.07

1.06

1.08

500

1 10

1 08

1.08

1.09

1.10

600

1.13

1 12

1.14

1.18

400

1.16

1.13

1 12

111

1.11

500

1.22

1.14

1.12

1. 12

1.13

600

1.18

1.16

1.18

M 118

400

1.06

1.07

1.08

LASER

500

600

1.09

1.10

1.07

1 09

1.07

1.10

1.08

1.12

1.10

1.15

400

1.07

1 06

1.07

1.09

500

1.09

1 07

1.07

1.08

1.11

600

1.11

1.14

1.18

400

1.10

1 09

1.08

1.09

1.11

500

1.12

1 10

110

111

1.14

600

1 14

1 13

114

1.17

1.22

400

1.17

1.15

1 14

1.16

500

1.19

1.16

115

1 16

1.18

600

1 20

1.17

118

1 21

1.25

BDU-33 B

400

1.18

1.16

1.18

1.20

1.24

(SUU-20 A)

500

600

1.22

1.29

1.21

1.27

1.19

1.29

1.25

1 37

1.32

1.45

400

1.22

1.20

1.19

1 24

1 28

500

1 26

1.23

1 24

1 28

1.37

600

1.33

1 31

1 34

1.40

1.50

400

1.28

1.25

1.29

1.34

500

1 33

1.30

1.34

1.42

600

1.40

1.39

1 42

1.58

400

1.45

1.38

1 39

1.39

1.41

500

1.49

1.43

1 42

1 46

1.51

600

1.58

1.50

151

1.58

1.66

BDU-33/B

400

1.13

1.14

1.17

1.22

(SUU-21A)

500

600

1.15

1.21

1 16

1 22

1.17

1.24

1.22

1.33

1.29

1.40

400

1.14

1.16

1.20

1.29

500

1.16

1.17

1.24

1.34

600

1.23

1.24

1 26

1.36

1.47

400

1.17

1.18

1.22

1.29

500

1.21

1.23

1.29

1.38

600

1 27

1.27

1.31

1.41

1.43

400

1 28

1,24

1.26

1.30

1.35

500

1 31

1 29

1.30

1 35

1.43

600

1.48

1 35

1,37

1.47

1.58

F4-34-VI-114-2

Figure 6-17 (Sheet 2 of 4) 9

6-53

UNCLASSIFIED

.O. 1F-4C-34-1-1

WRCS DRAG COEFFICIENTS

»F-4E I

FOR ALL BOMBS V, = 0 fps (0 Volts)

DIVE

RELEASE

5000

PICKLE SLANT RANGE (FEET)

TAS

BOMB

DEG

KTS

BELOW

7500

10,000

15,000

20,000

BDU-33A/B

400

1.12

1.13

1.14

1.24

(SUU-21/A)

500

600

1.15

1.17

1.15

1.17

1.16

1.18

1.21

1.23

1.27

1.28

400

1.14

1.15

1.20

1.24

500

1.16

1.15

1.16

1.21

1.28

600

1.19

1.18

1.19

1.25

1.30

400

1.17

1.16

1.17

1.20

1.25

500

1.19

1.18

1.19

1.23

1.28

600

1.22

1.20

1.21

1.25

1.31

400

1.27

1.24

1.27

1.31

500

1.30

1.26

1.28

1.32

600

1.31

1.27

1.30

1.34

BDU-33A B

400

1.18

1.17

1.18

1.21

1.25

(SUU-20/A)

500

600

1.22

1.25

1.20

1.22

1.18

1.23

1.24

1.27

1.29

1.33

400

1.22

1.20

1.24

1.27

500

1.25

1.22

1.25

1.31

600

1.29

1.25

1.29

1.34

400

1.28

1.24

1.26

1.30

500

1.32

1.27

1.26

1.28

1.32

600

1.35

1.30

1.29

1.31

1.36

400

1.44

1.37

1.36

1.38

500

1.48

1.40

1.37

1.38

1.40

600

1.51

1.42

1.39

1.40

1.42

ROCKEYE II
(8 BOMB RIPPLE)

500

550

1 1

1.40

1.41

FINNED BLU-27/B

400

1.01

1.03

1.05

500

1.01

1.03

1.05

1.09

1.11

600

1.02

1.05

1.07

1.11

1.15

400

1.01

1.03

1.05

1.07

1.09

500

1.01

1.03

1.05

1.08

1.10

600

1.02

1.05

1.08

1.14

1.19

400

1.01

1.03

1.04

1.07

1.09

500

1.00

1.03

1.04

1.08

1.11

600

1.06

1.10

1.17

1.24

400

1.02

1.03

1.06

1.08

500

1.02

1.04

1.08

1.13

600

1.06

1.11

1.20

1.29

UNFINNED

400

500

1.45

1.44

1.80

1.79

2.20

BLU-27/B

600

1.42

1.78

2.19

3.12

400

1.44

1.77

2.12

500

1.43

1.77

2.15

2.93

600

1.41

1.75

2.15

2.99

3.80

400

1.44

1.76

2.10

2.71

3.13

500

1.43

1.76

2.12

2.87

3.52

600

1.75

2.13

2.92

3.66

400

1.76

2.08

2.68

3.17

500

1.76

2.12

2.82

3.42

600

1.76

2.13

2.89

3.57

4 C - 34 - 1 - 1 - 099 — 3 )

Figure 6-17 (Sheet 3 of 4)

6-54

Change 4

VIRCS DRAG COEFFICIENTS

PICKLE

(CB)

SETTING

SLANT
RANGE 1000
(FEET)

DIVE

ANGLE

(DEG)

PULLUP

r&Jr&Mi-

*** ‘ I

• Each Cfi value is optimized for the ranges listed. Cb is based Qn a constant V e setting for all bombs. The V e potentiometer setting on the

ballistics computer must be adjusted to zero feet per second by the ground crew.

• The following ejector rack delay time bias settings must be used:

Tea * 95 msec
Teg and T ev * 75 msec

• Some aircraft may consistently experience a long or short bomb range impact error. A long range bias error may be compensated for by
positioning the pipper short of the target at pickle or by using the release advance control on the WRCS control panel. Short range bias

Figure 6-17 (Sheet 4 of 4)
'All data on page 6-56 deleted

6-55/(6-56 blank)

WRCS DRAG COEFFICIENTS j^B

M117 RETARDED

FOUR BOMB RIPPLE RELEASE 0.06 SEC RELEASE INTERVAL
RELEASE ADVANCE SETTING - 90 MILLISECONDS
4.0 G PULLOUT

PICKLE CONDITIONS
TRUE DIVE ALT

AIRSPEED ANG
(KNOTS) (DEG) (FT)

PICKLE TO
RELEASE
TIME
(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

BOMB

TIME

OF FALL
(SEC)

IMPACT

STICK

LENGTH

(FT)

SETTING

450

1000

2.10

652

- 7

5.8

190

2.65

1500

3.54

1113

+ 3

11.7

180

4.86

500

1000

1.98

621

- 8

5.0

190

2.51

1500

3.18

1034

- 1

10.1

190

4.70

550

1000

1.80

606

-10

4.4

180

2.39

1500

2.88

979

- 4

8.9

210

4.53

450

1500

1.56

923

-26

3.7

100

1.93

2000

2.04

1270

-23

6.5

140

2.81

2500

2.64

1610

-18

8.8

160

3.91

3000

3.24

1980

-14

11.8

170

5.16

3500

4.02

2380

- 9

15.0

170

6.53

4000

4.80

2800

- 3

18.5

160

7.98

500

2000

1.92

1230

-24

5.3

140

2.67

2500

2.40

1570

-21

7.8

160

3.76

3000

3.00

1900

-17

10.4

180

5.02

3500

3.66

2250

-13

13.3

180

6.41

4000

4.38

2630

- 8

16.4

180

7.91

4500

5.10

3068

- 3

19.6

180

9.47

550

2000

1.80

1190

-25

4.6

130

2.55

2500

2.22

1530

-23

6.9

160

3.61

3000

2.76

1840

-20

9.3

180

4.86

3500

3.36

2170

-16

11.9

190

6.26

4000

4.02

2510

-12

14.6

190

7.77

4500

4.68

2900

- 9

17.5

200

9.37

450

3500

2.28

2310

-36

8.8

140

3.97

4000

2.70

2620

-33

10.8

ISO

4.89

4500

3.06

2970

-30

12.9

160

5.87

5000

3.48

3310

-27

15.1

170

6.91

5500

3.90

3660

-24

17.4

170

7.98

6000

4.32

4030

-22

19.6

170

9.08

500

3500

2.16

2240

-38

7.8

140

3.83

4000

2.52

2550

-35

9.7

150

4.75

4S00

2.88

2870

-32

11.6

160

5.75

5000

3.24

3200

-30

13.6

170

6.81

5500

3.66

3520

-28

15.6

180

7.92

6000

4.02

3880

-25

17.8

180

9.08

550

4000

2.34

2500

-37

8.8

150

4.60

4500

2.70

2795

-35

10.4

160

5.61

5000

3.06

3100

-33

12.4

170

6.67

5500

3.42

3420

-31

14.3

180

7.81

6000

3.78

3740

-29

16.2

190

8.99

4C-34-1-1—(199-6)

Figure 6-17. WRCS DRAG COEFFICIENTS (Sheet 4A of 4)

Change 3

6-56A

T.O. 1F-4C-34-1-1

WRCS DRAG COEFFICIENTS

*F-4E

M117 RETARDED

FOUR BOMB RIPPLE RELEASE 0.10 SEC RELEASE INTERVAL
RELEASE ADVANCE SETTING - 150 MILLISECONDS
4.0 G PULLOUT

PICKLE CONDITIONS
TRUE DIVE ALT

AIRSPEED ANG
(KNOTS) (DEG) (FT)

PICKLE TO
RELEASE
TIME
(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

BOMB

TIME

OF FALL
(SEC)

IMPACT

STICK

LENGTH

(FT)

SETTING

450

1000

2.10

660

- 7

5.7

310

2.65

1500

3.50

1120

+ 3

11.7

290

4.86

500

1000

1.90

640

- 9

5.0

310

2.51

1500

3.20

1040

- 1

10.3

320

4.69

550

1000

1.80

610

-10

4.4

300

2.39

1500

2.90

980

- 4

9.0

350

4.51

450

30 1500

1.60

910

-26

3.7

170

1.93

2000

2.00

1280

-23

6.1

240

2.81

2500

2.60

1620

-19

8.8

270

3.90

3000

3.30

1960

-14

11.8

280

5.16

3500

4.00

2360

- 9

15.0

280

6.53

4000

4.80

2800

- 3

18.5

270

7.97

500

1500

1.70

810

-26

3.3

140

1.84

2000

1.90

1230

-24

5.3

220

2.67

2500

2.40

1570

-21

7.8

270

3.76

3000

3.00

2330

-17

10.4

290

5.02

3500

3.60

2260

-13

13.2

300

6.41

4000

4.30

2640

- 9

16.3

300

7.90

4500

5.10

3070

- 4

19.6

300

9.46

550

2000

1.80

1190

-25

4.6

210

2.55

2500

2.20

1540

-23

6.9

270

3.60

3000

2.80

1830

-20

9.3

300

4.85

3500

3.40

2150

-16

11.9

320

6.25

4000

4.00

2510

-13

14.6

320

7.76

4500

4.70

2892

- 8

17.5

320

9.36

450

3500

2.30

2300

-36

8.8

230

3.98

4000

2.70

2620

-33

10.8

250

4.91

4500

3.10

2960

-30

12.9

270

5.88

5000

3.50

3300

-27

15.1

280

6.91

5500

3.90

3670

-24

17.4

280

7.99

6000

4.30

4040

-21

19.7

290

9.09

500

3500

2.20

2220

-37

7.8

230

3.84

4000

2.50

2560

-35

9.7

250

4.75

4500

2.90

2860

-33

11.6

270

5.76

5000

3.20

3220

-31

13.7

290

6.82

5500

3.60

3550

-28

15.7

300

7.94

6000

4.00

3890

-26

17.8

300

9.09

550 45 4000 2.30

4500 2.70

5000 3.00

5500 3.40

6000 3.80

2530

-37

8.8

2800

-35

10.5

3130

-33

12.5

3430

-30

14.3

3730

-28

16.2

250 4.61
270 5.62
290 6.69
300 7.82
310 9.00

4C-34—1-1—(199-7)

Figure 6-17. WRCS DRAG COEFFICIENTS (Sheet 4B of 4)

6-56B

Change 3

T.O. 1F-4C-34-1-1

SEVEN BOMB RIPPLE RELEASE 0.06 SEC RELEASE INTERVAL
RELEASE ADVANCE SETTING - 180 MILLISECONDS
4.0 G PULLOUT

PICKLE CONDITIONS
TRUE DIVE ALT

AIRSPEED ANG

(KNOTS) (DEG) (FT)

PICKLE TO
RELEASE RELEASE

TIME ALTITUDE
(SEC) (FT)

BOMB

RELEASE TIME
ANGLE OF FALL
(DEG) (SEC)

IMPACT

STICK CB

LENGTH SETTING
(FT)

4S0

IS 1000

1.98

660

1500

3.18

1100

500

1000

1.86

640

1500

2.88

1040

450

1500

1.44

970

2000

1.92

1310

2500

2.40

1670

3000

2.94

2040

3500

3.60

2410

4000

4.32

2820

4500

5.10

3280

500

1500

1.38

930

2000

1.80

1270

2500

2.22

1630

3000

2.70

1980

3500

3.30

2310

4000

3.96

2680

4500

4.62

3090

5000

5.34

3540

5500

6.12

4040

450

45 3500

2.10

2400

4000

2.46

2730

4500

2.76

3100

5000

3.12

3450

5500

3.54

3790

6000

3.92

4150

6500

4.34

4520

7000

4.70

4930

7500

5.18

5320

8000

5.60

5740

500

45 3500

1.98

2340

4000

2.28

2680

4500

2.58

3020

5000

2.94

3350

5500

3.30

3680

6000

3.68

4010

6500

4.04

4360

7000

4.40

4730

7500

4.76

5110

- 8

5.3

390

2.19

+ 1

10.6

380

3.77

-10

4.6

380

2.10

- 3

9.3

430

3.65

-26

3.5

190

1.70

-23

5.6

280

2.31

-20

8.2

330

3.09

-16

10.9

350

3.98

-12

13.7

350

4.93

- 7

16.8

350

5.97

- 1

20.3

330

7.03

-27

3.0

170

1.63

-24

4.9

265

2.22

-22

7.2

330

2.97

-19

9.7

360

3.87

-16

12.1

370

4.82

-11

15.0

380

5.90

- 7

17.8

380

7.02

- 2

21.1

360

8.17

+ 3

24.6

350

9.32

-37

8.1

280

3.11

-34

10.0

310

3.75

-32

11.9

330

4.45

-30

13.9

340

5.19

-27

16.0

350

5.95

-24

18.0

360

6.71

-21

20.2

360

7.51

-19

22.4

360

8.30

-IS

24.8

360

9.10

-12

27.2

350

9.87

-39

7.2

270

3.00

-37

8.9

300

3.65

-35

10.8

330

4.35

-32

12.6

340

5.11

-30

14.5

360

5.89

-28

16.3

370

6.68

-25

18.3

380

7.52

-23

20.4

380

8.38

-21

22.4

390

9.24

4C-34-l-l-<«*-«)

WRCS DRAG COEFFICIENTS (Sheet 4C of 4)

Figure 6-17.

Change 3

6-56C

T.O. 1F-4C-34-1-1

MK 82 SNAKEYE I (RETARDED)

SEVEN BOMB RIPPLE RELEASE 0.10 SEC RELEASE INTERVAL
RELEASE ADVANCE SETTING - 300 MILLISECONDS
4.0 G PULLOUT

PICKLE

CONDITIONS

PICKLE TO

BOMB

IMPACT

TRUE

DIVE

ALT

RELEASE

TIME

STICK

AIRSPEED

ANG

TIME

ALTITUDE

ANGLE OF FALL

LENGTH

SETTING

(KNOTS)

(DEG)

(FT)

(SEC)

(FT)

(DEG)

(SEC)

(FT)

450

1000

1500

2.00

3.20

660

1100

- 8
+ 1

5.3

10.7

640

630

2.18

3.77

500

1000

1.80

650

-10

4.6

620

2.09

1S00

2.90

1040

- 3

9.3

690

3.64

450

1500

1.50

950

-26

3.5

320

1.69

2000

1.90

1310

-24

5.6

470

2.30

2500

2.40

1670

-20

8.1

550

3.08

3000

3.00

2030

-16

10.9

580

3.97

3500

3.60

2410

-12

13.7

590

4.93

4000

4.30

2820

- 7

16.8

580

5.96

4500

5.10

3280

- 1

20.3

550

7.03

500

1500

1.40

920

-27

3.0

280

1.62

2000

1.80

1270

-25

4.9

440

2.20

2500

2.20

1630

-22

7.2

550

2.97

3000

2.70

1980

-19

9.6

600

3.86

3500

3.30

2320

-15

12.1

620

4.82

4000

3.90

2693

-12

14.9

630

5.89

4500

4.60

3100

- 7

17.9

620

7.02

5000

5.30

3540

- 3

21.0

610

8.17

5500

6.10

4050

+ 2

24.6

580

9.32

450

3500

2.10

2400

-37

8.1

460

3.10

4000

2.50

2710

-34

9.9

510

3.75

4500

2.80

3080

-32

11.9

540

4.45

5000

3.10

3460

-30

13.9

570

5.18

5500

3.50

3810

-27

16.0

580

5.95

6000

3.90

4170

-24

18.1

590

6.73

6500

4.30

4550

-21

20.3

600

7.53

7000

4.70

4940

-18

22.5

600

8.33

7500

5.10

5350

-16

24.8

590

9.12

8000

5.60

5730

-12

27.2

590

9.87

500

3500

2.00

2330

-39

7.2

440

3.00

4000

2.30

2660

-37

8.9

500

3.64

4500

2.60

3010

-35

10.7

540

4.35

5000

2.90

3360

-33

12.6

570

5.10

5500

3.30

3680

-30

14.5

600

5.89

6000

3.60

4050

-28

16.4

610

6.71

6500

4.00

4390

-25

18.4

630

7.55

7000

4.40

4740

-23

20.4

640

8.41

7500

4.80

5110

-20

22.5

640

9.27

4C—34—1—1—(1S9-9)

Figure 6-17. WRCS DRAG COEFFICIENTS (Sheet 4D of 4)

6-56D

Change 3

EXPOSURE TIME CHART

• These time exposure data assume that a 4.0 G recovery is
attained 2.0 seconds after release. The G is maintained until
a 30 degree climb out is attained.

NO POWER ADVANCE WAS ASSUMED UNTIL THE NOSE
OF THE AIRCRAFT PASSED THROUGH THE HORIZON.
MAXIMUM POWER WAS APPLIED AS THE NOSE OF THE
AIRCRAFT PASSED THROUGH THE HORIZON.

'•*1 ”

4 s The values listed for altitude lost during pullout are
based on a starting altitude of 7000 feet.

DIVE ANGLE - 45°; ROLL IN ALTITUDE - 12,000 FT; RELEASE ALTITUD
4.0 G RECOVERY WITH A 30° CLIMB OUT ANGLE.

E - 7,000 FI

;

EXPOSURE TIME IN SECONDS

RE LEASE

ALTITUDt

TAS

COST

BELOW

KTS

DURING PULLOUT

9500 FT

8500 FT

7500 FT

6500 FT

5500 FT

4500 FT

450

2420

26.3

22.0

17.7

13.3

8.8

—

500

2920

26.4

22.6

18.8

15.0

11.0

5.9

550

3450

27.0

23.5

20.1

16.6

13.0

8.9

5.0 G RECOVERY WITH A 30° CLIMB OUT ANGLE

450

1910

24.5

19.6

14.9

10.3

5.2

—

500

2310

23.4

19.4

15.7

11.4

7.2

—

550

2730

23.4

19.8

16.2

12.6

8.9

3.8

Figure 6-18 (Sheet 1 of 2)

(6-56E blank)/6-56F

Change 3

EXPOSURE TIME CHART M

FOR LOFT BOMBING

APPROACH

TAS-

KNOTS

TIME TO PERFORM MANEUVER AND ESCAPE

EXP. TIME
ABOVE 500 FT
SECONDS

EXP. TIME
ABOVE 1000 FT
SECONDS

EXP. TIME
ABOVE 1500 FT
SECONDS

EXP. TIME
ABOVE 2000 FT
SECONDS

MAX ALT.
GAINED
FEET

HORIZONTAL RANGE A/C
TO TGT. AT BOMB IMPACT
FEET

—

1419

1880

4896

7235

2359

9763

400

2855

12457

3384

14988

3936

17153

4389

18903

450

1523

5865

2201

8813

2759

12073

3498

15458

3956

18725

4682

21872

5453

24562

NOTE: This chart is based on an approach altitude of 300 feet. For other approach altitudes,
add the difference to the Exposure Time altitude valves stated on this chart, i.e. for
a 500-foot approach, the difference (500-300) is +200 feet. The exposure time above
700 is obtained from the Exposure Time above 500 feet column.

EXAMPLE 1:

Approach altitude: 300 feet
Approach TAS: 300 knots

Release Angle: 15 degrees

FIND:

Exposure Time above 500 feet: 14 seconds
Maximum Altitude Gained: 1050 feet

Horizontal Range from
Aircraft to Target

at Bomb Impact: 2563 feet

EXAMPLE 2:

Approach altitude: 500 feet
Approach TAS: 300 knots

Release Angle: 15 degrees

FIND:

Exposure Time above 700 feet: 14 seconds
Maximum Altitude Gained: 1050 feet

Horizontal Range from Aircraft
to Target at Bomb Impact: 2563 feet

F 4 . 34 - VM 15

Figure 6-18 (Sheet 2 of 2)

6-57

T.O. 1F-4C-34-1-1

Note Correction is given for the R2 + R 3 range
in seconds and is applied to the pullup
timer. (Headwind Add, Tailwind Subtract)

F 4 . 34 .VM 16

Figure 6-19

6-58

T.O. 1F-4C-34-1-1

WRCS BALLISTIC BATA (C.P. BOMBS)

2.0 G PULLOUT
0. 06 SEC RELEASE INTERVAL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

KNOTS

TAS

DIVE

ANCLE

(DEG)

SLANT
RANGE
(1000 FT)

ALT

AGL

(FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALT

(FT)

RELEASE

ANGLE

(DEG)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

450

3420

4.34

2440

-12

8.2

120

300

430

670

5130

6.02

3920

- 8

12.6

210

380

530

840

6840

7.82

5490

- 4

17.0

170

420

590

930

5000

3.92

3600

-23

8.2

100

240

340

540

7500

5.36

5680

-19

12.3

130

320

460

710

10000

6.74

7830

-16

16.4

ISO

380

540

840

7070

3.24

5330

-39

8.3

200

280

440

10610

4.26

8350

-36

12.4

110

280

390

610

14140

5.22

11420

-34

16.3

140

340

480

750

500

3420

3.98

2390

-14

7.4

120

290

410

640

5130

5.54

3820

-10

11.4

ISO

380

530

840

6840

7.10

5320

- 7

15.3

180

440

610

960

5000

3.68

3510

-24

7.4

230

320

510

7500

4.94

5580

-21

11.2

130

320

440

690

10000

6.26

7680

-18

15.0

150

380

530

830

7070

3.06

5239

-40

7.6

190

260

410

10610

4.02

8230

-37

11.5

110

260

370

580

14140

4.98

11240

-35

15.2

130

330

460

710

550

3420

3.74

2330

-15

6.7

280

390

620

5130

5.18

3730

-12

10.4

150

370

520

820

6840

6.62

5190

- 9

14.1

180

440

620

970

5000

3.44

3460

-25

6.8

220

310

480

7500

4.70

5460

-22

10.4

120

300

420

660

10000

5.96

7510

-20

14.0

150

370

510

810

7070

2.94

5130

-41

7.0

170

240

380

10610

3.84

8100

-38

10.7

100

250

350

540

14140

4.80

11050

-36

14.4

120

310

430

680

600

3420

3.56

2270

-15

6.2

270

380

590

5130

4.88

3650

-13

9.7

150

360

510

800

6840

6.26

5070

-10

13.2

170

430

600

950

5000

3.26

3400

-26

6.3

210

290

450

7500

4.52

5340

-23

9.7

290

400

630

10000

5.72

7370

-21

13.3

140

350

490

770

7070

2.82

5050

-41

6.5

160

230

360

10610

3.72

7960

-39

10.2

230

330

510

14140

4.68

10860

-37

13.7

120

290

410

640

F 4 - 34 - VI - 117-1

Figure 6-20 (Sheet 1 of 9)

6-59

T.O. 1F-4C-34-1-1

WRCS BALLISTIC DATA (GP BOMBS) continued

3.9 G PULLOUT
0. 06 SEC RELEASE INTERVAL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

KNOTS

TAS

DIVE

ANGLE

(DEG)

SLANT
RANGE
(1000 FT)

ALT

ACL

(FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALT

(FT)

RELEASE

ANGLE

(DEG)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

3420

3.16

2740

-10

9.5

200

490

690

1080

5130

4.30

4340

- 4

14.7

240

590

830

1300

6840

5.56

6030

♦ 2

20.2

250

630

880

1380

5000

2.88

3990

-21

9.3

160

400

560

870

7500

3.84

6250

-16

14.1

210

520

720

1140

10000

4.80

8560

-12

18.9

240

590

820

1300

7070

2.46

5770

-38

9.2

130

320

450

710

10610

3.12

8000

-34

13.7

180

440

620

970

14140

3.78

12240

-31

18.0

210

530

750

1180

son

3420

2.02

2690

-12

8.5

190

480

670

1050

5130

3.04

4250

- 8

13.2

240

610

850

1330

6840

5.02

5880

- 3

18.0

270

670

940

1480

5000

2.70

3930

-23

8.4

150

380

530

830

7500

3.60

6150

-19

12.8

200

510

710

1120

10000

4.44

8430

-15

17.2

240

600

840

1320

7070

2.34

5690

-39

8.4

120

300

420

660

10610

3.00

8870

-36

12.6

170

420

590

930

14140

3.60

12100

-33

16.8

210

520

730

1140

550

3420

2.74

2640

-13

7.7

190

460

650

1020

5130

3.70

4170

-10

12.1

240

610

850

1330

6840

4.66

5760

- 6

16.4

280

690

970

1530

5000

2.58

3860

-24

7.7

140

360

500

790

7500

3.36

6080

-21

11.8

200

490

690

1080

10000

4.20

8310

-17

16.0

240

590

830

1300

7070

2.22

5620

-40

7.7

110

280

390

610

10610

2.88

8760

-37

11.8

160

400

560

880

14140

3.48

11950

-35

15.8

200

490

690

1090

6on

3420

2.62

2590

-14

7.1

180

440

620

970

5130

3.52

4100

-11

11.2

240

590

830

1300

6840

4.42

5660

- 8

15.3

280

690

970

1520

5000

2.46

3800

-25

7.1

140

340

470

740

7500

3.24

5980

-22

11.1

190

470

660

1030

10000

4.02

8200

-19

15.1

230

570

790

1250

7070

2.16

5530

-41

7.2

100

260

370

570

10610

2.76

8670

-38

11.2

150

370

520

820

14140

3.36

11820

-36

15.1

210

470

650

1030

F4-34-VI-I17-2

6-60

^ Figure 6-20 (Sheet 2 of 9)

T.O. 1F-4C-34-1-1

WRCS BALLISTIC DATA (GP BOMBS) continued

4. 0 G PULLOUT
0.06 SEC RELEASE INTERVAL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

KNOTS

TAS

DIVE

ANCLE

(DEG)

SLANT
RANGE
(1000 FT)

ALT

AGL

(ET)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALT

(FT)

RELEASE

ANGLE

(DEG)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

450

3420

2.58

2870

- 9

10.1

270

660

930

1460

5130

3.48

4510

- 2

15.9

310

770

1080

1700

6840

4.50

6240

+ 5

22.0

310

770

1080

1700

5000

2.42

4160

-20

9.9

220

540

760

1200

7500

3.14

6500

-IS

15.1

280

690

970

1520

10000

3.92

8880

- 9

20.3

300

750

1050

1660

7070

2.10

5970

-37

9.6

180

440

610

950

10610

2.58

9280

-33

14.3

240

590

830

1310

14140

3.12

12600

-29

18.9

280

710

990

1560

500

3420

2.40

2820

-11

9.1

260

650

920

1440

5130

3.18

4430

- 6

14.1

330

820

1140

1800

6840

4.02

6100

- 1

19.4

350

880

1230

1930

5000

2.24

4120

-22

8.9

210

520

730

1140

7500

2.90

6420

-18

13.6

280

690

960

1520

10000

3.56

8770

-14

18.3

320

800

1120

1760

7070

1.98

5910

-39

8.7

160

400

560

870

10610

2.46

9190

-35

13.2

230

570

800

1260

14140

2.94

12490

-32

17.5

280

700

980

1540

550

3420

2.28

2780

-13

8.2

260

640

890

1400

5130

3.00

4360

- 8

12.9

330

830

1160

1820

6840

3.72

6000

- 4

17.6

380

940

1310

2060

5000

2.18

4040

-23

8.1

200

500

690

1080

7500

2.78

6340

-20

12.5

270

680

950

1490

10000

3.38

8660

-16

16.9

320

810

1130

1770

7070

1.92

5830

-39

8.1

150

370

510

800

10610

2.40

9080

-37

12.3

220

550

760

1200

14140

2.82

12380

-34

16.5

270

670

940

1480

600

3420

2.22

2720

-14

7.6

250

620

860

1350

5130

2.88

4300

-10

12.0

330

810

1140

1790

6840

3.54

5910

- 6

16.3

380

940

1320

2070

5000

2.06

4000

-24

7.5

190

460

640

1000

7500

2.66

6260

-21

11.7

260

650

900

1420

10000

3.26

8560

-18

16.0

310

780

1090

1720

7070

1.86

5750

-40

7.5

140

340

470

730

10610

2.34

8970

-38

11.7

210

520

720

1130

14140

2.76

12250

-35

15.8

260

640

900

1410

F 4 - 34 - VI - 117*3

Figure 6-20 (Sheet 3 of 9)

6-61

T.O. 1F-4C-34-1-1

WRCS BALLISTIC VATA(6P BOMBS) continued

2.0 G PULLOUT
0.10 SEC RELEASE INTERVAL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

KNOTS

TAS

DIVE

ANGLE

(DEG)

SLANT
RANGE
(1000 FT)

ALT

AGL

(FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALT

(FT)

RELEASE

ANGLE

(DEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

450

3420

4.30

2450

-12

8.2

200

500

700

1110

5130

6.00

3030

- 8

12.6

250

630

880

1390

6840

7.80

5490

- 4

17.0

280

700

990

1550

5000

3.00

3600

-23

8.2

160

410

570

890

7500

5.40

5670

-19

12.3

220

540

760

1190

10000

6.80

7820

-16

16.4

260

640

890

1410

7070

3.30

5300

-39

8.3

130

330

470

730

10610

4.30

8330

-36

12.4

180

460

650

1020

14140

5.20

11430

-34

16.3

230

570

790

1250

500

3420

4.00

2370

-14

7.4

200

490

680

1070

5130

5.50

3820

-10

11.4

250

630

890

1390

6840

7.10

5320

- 7

15.3

290

730

1020

1600

5000

3.70

3510

-24

7.4

ISO

390

540

850

7500

5.00

5560

-21

11.2

210

530

740

1150

10000

6.30

7670

-18

15 .0

250

630

880

1390

7070

3.10

5220

-40

7.6

120

310

440

680

10610

4.00

8240

-37

11.5

170

440

610

960

14140

5.00

11230

-35

15.2

220

540

760

1190

550

3420

3.70

2340

-15

6.7

190

470

650

1030

5130

5.20

3720

-12

10.4

250

620

870

1370

6840

6.60

5190

- 9

14.1

290

730

1020

1610

5000

3.50

3430

-25

6.7

150

360

510

800

7500

4.70

5460

-22

10.4

200

500

700

1110

10000

5.90

7530

-20

14.0

240

610

850

1340

7070

2.00

5160

-41

7.0

120

200

410

640

10610

3.00

8060

-38

10.7

170

410

580

910

14140

4.80

11050

-36

14.4

210

510

720

1130

600

3420

3.50

2290

-15

6.2

180

440

620

980

5130

4.00

3640

-13

0.7

240

600

840

1330

6840

6.30

5060

-10

13.2

290

720

1010

1580

5000

3.30

3380

-26

6.2

140

210

480

750

7500

4.50

5350

-23

9.7

190

480

670

1050

10000

5.70

7370

-21

13.3

230

580

820

1280

7070

2.80

5060

-41

6.5

110

270

380

600

10610

3.70

7980

-39

10.2

160

390

540

850

14140

4.70

10850

-37

13.7

200

490

680

1070

F 4 - 34 - VI - 117-4

| Figure 6-20 (Sheet 4 of 9)

6-62

T.O. 1F-4C-34-1-1

WRCS BALLISTIC BATA (GP BOMBS) continued

3.0 G PULLOUT
8.10 SEC RELEASE INTERVAL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

KNOTS

TAS

DIVE

ANGLE

(DEG)

SLANT
RANGE
(1000 FT)

ALT

AGL

(FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALT

(FT)

RELEASE

ANGLE

(DEG)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

450

3420

3.20

2730

-10

9.6

330

820

1150

1810

5130

4.30

4340

- 4

14.7

400

990

1380

2170

6840

5.50

6030

+ 1

20.0

420

1040

1460

2300

5000

2.90

3990

-21

9.3

270

660

920

1450

7500

3.80

6260

-17

14.1

340

860

1200

1880

10000

4.80

8560

-12

18.8

390

980

1370

2160

7070

2.50

5750

-37

9.2

210

540

750

1180

10610

3.10

9000

-34

13.6

290

730

1030

1610

14140

3.80

12230

-31

18.0

360

890

1250

1960

500

3420

2.90

2690

-12

8.5

320

790

1110

1750

5130

3.90

4250

- 8

13.0

400

1000

1410

2210

6840

5.00

5880

- 3

18.0

450

1120

1570

2460

5000

2.60

3960

-23

8.4

250

630

880

1380

7500

3.60

6150

-19

12.8

340

850

1180

1860

10000

4.40

8440

-15

17.1

400

1000

1390

2190

7070

2.30

5710

-39

8.4

200

500

700

1080

10610

3.00

8870

-36

12.6

280

700

980

1540

14140

3.60

12090

-33

16.7

350

860

1210

1900

550

3420

2.80

2630

-13

7.8

310

770

1080

1710

5130

3.70

4170

-10

12.1

410

1010

1410

2220

6840

4.60

5760

- 6

16.3

460

1150

1610

2540

5000

2.60

3850

-24

7.7

240

600

840

1320

7500

3.40

6060

-21

11.8

330

820

1140

1800

10000

4.20

8310

-17

16.0

390

980

1380

2160

7070

2.20

5630

-40

7.7

190

470

650

1000

10610

2.90

8740

-37

11.8

270

660

930

1460

14140

3.50

11930

-35

15.8

330

820

1150

1810

600

3420

2.CO

2520

-14

7.1

290

730

1030

1610

5130

3.50

4100

-11

11.2

390

980

1370

2160

6840

4.40

5660

- 8

15.3

460

1150

1610

2530

5000

2.50

3790

-25

7.1

230

560

790

1240

7500

3.30

5960

-22

11.1

310

780

1100

1720

10000

4.00

8210

-19

15.1

380

940

1320

2080

7070

2.20

5500

-40

7.2

180

440

600

930

10610

2.80

8640

-38

11.2

250

620

870

1370

14140

3.40

11800

-36

15.1

310

780

1090

1720

F4-34-VI-117-5

Figure 6-20 (Sheet 5 of 9)

6-63

T.O. 1F-4C-34-1-1

WRCS BALLISTIC DATA (GP BOMBS) continued

4.0 G PULLOUT
0.10 SEC RELEASE INTERVAL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELE

ASE

KNOTS

TAS

DIVE

ANGLE

(DEG)

SLANT
RANGE
(1000 FT)

ALT

AGI.

(FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALT

(FT)

RELEASE

ANGLE

(DEG)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

bomb

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

4^0

3420

2.60

2870

- 9

10.2

450

1100

1550

2430

5130

3.50

4510

- 2

15.9

520

1290

1800

2830

6840

4.50

6240

♦ 5

22.0

510

1280

1800

2810

5000

2.40

4170

-20

9.8

360

900

1260

1960

7500

3.10

6500

-15

15.0

460

1140

1600

2510

10000

3.90

8880

- 9

20.3

500

1250

1750

2750

7070

2.10

5970

-37

9.5

290

720

990

1530

10610

2.60

9280

-33

14.3

400

990

1380

2180

14140

3.10

12610

-30

18.9

470

1180

1650

2590

snn

3420

2.40

2820

-11

9.0

440

1080

1520

2370

5130

3.20

4430

- 6

14.1

550

1360

1900

2990

6840

4.00

6100

- 1

19.3

590

1460

2050

3220

5000

2.30

4100

-22

8.9

350

870

1210

1880

7500

2.90

6420

-18

13.6

460

1150

1600

2520

10000

3.60

8760

-13

18.3

540

1340

1870

2940

7070

2.00

5900

-38

8.7

270

660

910

1410

10610

2.50

9170

-35

13.2

380

960

1340

2100

14140

2.90

12510

-32

17.5

470

1160

1630

2570

550

3420

2.30

2770

-13

8.2

430

1060

1480

2300

5130

3.00

4360

- 8

12.8

550

1370

1920

3020

6840

3.70

6000

- 4

17.5

620

1550

2170

3410

5000

2.20

4040

-23

8.1

330

820

1140

1770

7500

2.80

6330

-10

12.5

450

1120

1570

2470

10000

3.40

8660

-16

17.0

540

1340

1880

2950

7070

1.90

5840

-40

8.1

240

600

830

1280

10610

2.40

9070

-37

12.3

360

910

1270

1980

14140

2.80

12390

-34

16.5

450

1120

1570

2460

Ann

3420

2.20

2730

-14

7.6

410

1010

1400

2180

5130

2.90

4290

-10

12.0

550

1360

1900

2980

6840

3.50

5920

- 7

16.2

630

1560

2180

3420

■to

5000

2.10

3990

-24

7.5

310

760

1060

1640

7500

2.70

6250

-21

11.8

430

1080

1510

2370

10000

3.30

8550

-18

16.0

520

1300

1820

2870

7070

1.90

5720

-40

7.5

230

560

780

1200

10610

2.30

9000

-38

11.7

340

850

1190

1850

14140

2.80

12220

-35

15.8

430

1670

1500

2350

F4-34-VI-117-6

6-64

Figure 6-20 (Sheet 6 of 9)

T.O. 1F-4C-34-1-1

WRCS BALLISTIC BATA ( OP BOMBS) continued

% V

v vi

2.0 G PULLOUT
0. 14 SEC RELEASE INTERVAL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

KNOTS

TAS

DIVE

ANGLE

(DEG)

SLANT
RANGE
(1000 FT)

ALT

AGL

(FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALT

(FT)

RELEASE

ANGLE

(DEG)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

450

3420

4.28

2450

-12

8.2

280

700

980

1540

5130

6.10

3910

- 8

12.6

360

890

1240

1950

6840

7.78

5490

- 4

17.0

390

980

1380

2160

5000

3.98

3580

-23

8.2

230

570

800

1250

7500

5.38

5670

-19

12.3

300

760

1060

1670

10000

6.78

7820

-16

16.4

360

890

1250

1960

7070

3.20

5350

-39

8.3

190

470

650

1030

10610

4.32

8320

-36

12.4

260

650

910

1420

14140

5.30

11380

-33

16.3

320

790

1110

1750

500

3420

4.00

2380

-14

7.4

270

680

950

1500

5130

5.54

3820

-10

11.4

360

890

1240

1950

6840

7.08

5320

- 7

15.3

410

1020

1420

2240

5000

3.70

3510

-24

7.4

220

540

750

1190

7500

4.96

5570

-21

11.2

290

730

1030

1610

10000

6.22

7690

-18

15.0

350

880

1230

1940

7070

3.06

5240

-40

7.6

170

440

610

960

10610

4.04

8220

-37

11.5

250

610

860

1350

14140

5.02

11210

-35

15.2

300

760

1060

1670

550

3420

3.72

2340

-15

6.7

260

6S0

910

1440

5130

5.12

3736

-12

10.4

350

870

1220

1910

6840

6.66

5180

- 9

14.1

410

1030

1440

2260

5000

3.42

3460

-25

6.8

200

510

710

1120

7500

4.68

5470

-22

10.4

280

700

980

1550

10000

5.°4

7520

-20

14.0

340

850

1200

1880

7070

2.92

5150

-41

7.0

160

410

570

890

10610

3.90

8060

-38

10.7

230

580

810

1270

14140

4.74

11080

-36

14.4

290

720

1010

1580

600

3420

3.58

2270

-15

6.1

250

620

870

1370

5130

4.84

3660

-13

9.6

340

840

1180

1850

6840

6.24

5070

-11

13.2

400

1000

1400

2200

5000

3.28

3390

-26

6.3

190

480

670

1050

7500

4.54

5330

-23

9.7

270

670

930

1470

10000

5.66

7390

-21

13.3

320

820

1140

1800

7070

2.78

5070

-41

6.6

150

380

530

830

10610

3.76

7940

-39

10.1

220

540

760

1100

14140

4.74

10820

-37

13.7

270

680

950

1500

F4-34-VI-117*7

6-65

Figure 6-20 (Sheet 7 of 9)

T.O. 1F-4C-34-1-1

WRCS BALLISTIC DATA (CP BOMBS) continued

3.0 G PULLOUT
B.14 SEC RELEASE INTERVAL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

KNOTS

TAS

DIVE

ANGLE

(DEG)

SLANT
RANGE
(1000 FT)

ALT

AGL

(FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALT

(FT)

RELEASE

ANGLE

(DEG)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

BOMB

STICK

LENGTH

(FT)

450

3420

3.14

2740

-10

9.5

460

1130

1590

2500

5130

4.26

4340

- 5

14.6

550

1370

1920

3010

6840

5.52

6020

+ 1

20.0

580

1450

2040

3220

5000

2.00

3980

-21

9.3

370

920

1290

2030

7500

3.88

6230

-16

14.1

480

1200

1680

2640

10000

4.86

8550

-12

18.9

550

1370

1920

3020

7070

2.46

5770

-38

9.2

300

750

1040

1610

10610

3.16

8970

-34

13.6

410

1030

1440

2260

14140

3.86

12200

-31

18.0

500

1250

1740

2740

500

3420

3.00

2670

-12

8.6

450

1120

1570

2470

5130

3.98

4240

- 7

13.2

570

1410

1980

3100

6840

4.96

5870

- 3

17.9

630

1560

2180

3430

5000

2.76

3910

-22

8.4

350

880

1230

1940

7500

3.60

6150

-19

12.8

480

1180

1650

2600

10000

4.44

8430

-15

17.1

560

1390

1950

3060

7070

2.32

5700

-39

8.4

280

690

960

1480

10610

3.02

8850

-36

12.6

390

980

1370

2160

14140

3.58

12100

-33

16.7

480

1200

1680

2650

550

3420

2.72

2640

-13

7.7

430

1060

1490

2340

5130

3.70

4170

-10

12.0

570

1400

1970

3090

6840

4.68

5750

- 6

16.4

650

1620

2260

3560

5000

2.62

3840

-24

7.7

340

830

1170

1820

7500

3.32

6090

-21

11.8

460

1130

1590

2490

10000

4.16

8320

-18

15.9

550

1370

1910

3010

7070

2.32

5560

-40

7.7

260

650

900

1380

10610

2.88

8750

-37

11.8

370

930

1290

2040

14140

3.44

11960

-35

15.8

460

1150

1600

2520

3420

2.58

2600

-14

7.1

410

1020

1430

2220

5130

3.56

4090

-11

11.2

560

1380

1930

3030

6840

4.40

5650

- 8

15.3

650

1600

2240

3530

5000

2.48

3790

-25

7.1

320

780

1100

1700

7500

3.32

5950

-22

11.1

440

1090

1530

2410

10000

. 4.02

8190

-19

15.1

530

1320

1850

2900

7070

2.18

5520

-41

7.2

240

600

820

1260

10610

2.74

8680

-38

11.2

350

870

1220

1910

14140

3.44

11770

-36

15.1

440

1090

1530

2400

f 4-34-VI-l 17-8

^ Figure 6-20 (Sheet 8 of 9)

6-66

T.O. 1F-4C-34-1-1

WRCS BALLISTIC BATA (GP BOMBS) continued

4.0 G PULLOUT
0.14 SEC. RELEASE INTERVAL

PICKLI

CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

PICKLE

TIME

KNOTS

DIVE

SLANT

ALT

RELEASE

BOMB

RO\lR

TAS

ANGLE

RANGE

AGL

RELEASE

ALT

ANGLE

STICK

(DEG)

(1000 FT)

(FT)

TIME

(FT)

(DEG)

IMPACT

LENGTH

(SEC)

(FT)

4S0

3420

2.60

2860

- 9

10.1

620

1530

2150

3350

5130

3.44

4510

- 3

15.7

720

1790

2510

3930

6840

4.56

6240

+ 5

22.1

720

1800

2520

3930

5000

2.36

4180

-21

9.8

500

1240

1720

2660

7500

3.20

6480

-15

15.1

650

1610

2250

3540

10000

3.90

8870

- 9

20.2

710

1760

2460

3850

7070

2.16

5940

-37

9.6

410

990

1380

2110

10610

2.58

9280

-34

14.2

550

1380

1930

3000

14140

3.14

12580

-30

18.9

660

1650

2310

3620

500

3420

2.46

2810

-11

9.1

620

1530

2130

3300

5130

3.16

4430

- 6

14.0

760

1880

2640

4140

6840

4.00

6090

- 1

19.2

820

2050

2860

4500

5000

2.22

4120

-22

8.8

480

1170

1620

2500

7500

2.92

6410

-18

13.5

640

1600

2240

3520

10000

3.62

8750

-13

18.3

750

1870

2610

4100

7070

2.02

5880

-38

8.7

380

900

1250

1920

10610

2.44

9200

-36

13.1

530

1330

1850

2850

14140

3.00

12460

-32

17.5

660

1630

2290

3600

550

3420

2.32

2760

-13

8.2

600

1470

2040

3160

5130

3.02

4350

- 8

12.8

780

1920

2680

4210

6840

3.72

5990

- 4

17.5

870

2170

3030

4760

5000

2.22

4030

-23

8.1

470

1130

1570

2420

7500

2.78

6330

-18

12.5

630

1560

2190

3430

10000

3.34

8670

-16

16.8

750

1860

2600

4080

7C7C

1.8S

5850

-40

8.0

330

810

1120

1720

10610

2.44

9050

-36

12.3

510

1270

1770

2730

14140

2.86

12350

-34

16.5

630

1570

2190

3450

600

3420

2.18

2730

-14

7.5

570

1370

1900

2940

5130

2.88

4290

-10

11.9

760

1870

2630

4130

6840

3.58

5900

- 6

16.4

880

2190

3060

4800

5000

2.08

3990

-24

7.5

430

1030

1430

2210

7500

2.64

6270

-21

11.7

600

1490

2080

3250

10000

3.34

8530

-18

16.0

730

1820

2550

4000

7070

1.88

5740

-40

7.5

310

760

1050

1610

10610

2.30

9000

-38

11.6

480

1180

1640

2510

14140

2.86

12180

-35

15.7

600

1500

2090

3290

F4-34-VI.117-9

Figure 6-20 (Sheet 9 of 9)

6-67

T.O. 1F-4C-34-1-1

VIVE TOSS RIPPLE RELEASE

MK20 MOD 2 & MOD 3 (ROCKEYE II)

2.0 C PULLOUT
0.10 SEC RELEASE INTERVAL
FUZE FUNCTION TIMS - 6.0 SEC

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN
MPI* OF FIRST AND
LAST CLUSTER

V/RCS

C D

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

ALTITUDE

_nm_ 1

TIME

RFLEASE

IMPACT

(EEC)

BOMB

STICK

(FT)

BON®

STICK

(FT)

450

4000

11700

5.7

2840

1590

13.3

490

1070

1.51

4500

13160

6.8

3230

2170

16.3

480

1060

1.78

5000

14620

8.0

3650

2810

19.5

470

1040

2.10

500

4000

11700

5.1

2770

1280

11.5

500

1120

1.43

4500

13160

6.0

3130

1790

14.2

520

1140

1.67

5000

14620

7.1

3500

2350

17.1

520

1130

1.96

5500

16080

8.2

3900

2940

20.0

510

1120

2.28

550

4000

11700

4.7

2700

1000

10.0

520

1140

1.35

4500

13160

5.4

3060

1480

12.5

540

1190

1.55

5000

14620

6.3

3410

1970

15.0

560

1210

1.81

5500

16080

7.3

3760

2500

17.7

550

1210

2.11

6000

17540

8.3

4150

3060

20.4

540

1200

2.44

450

4500

9000

3.8

3140

840

8.5

380

840

1.21

5000

10000

4.3

3490

1270

10.2

420

910

1.30

5500

11000

4.8

3840

1700

12.0

440

970

1.44

6000

12000

5.4

4170

2130

14.0

460

1010

1.60

6500

13000

6.0

4520

2570

16.0

470

1030

1.80

7000

14000

6.7

4850

3020

18.1

480

1150

2.02

500

5000

10000

3.9

3440

960

8.8

400

880

1.25

5500

11000

4.4

3770

1360

10.4

430

960

1.36

6000

12000

4.8

4140

1780

12.2

460

1010

1.50

6500

13000

5.4

4440

2190

14.1

480

1060

1.67

7000

14000

6.0

4760

2600

15.9

500

1090

1.87

7500

15000

6.6

5090

3020

17.8

510

1110

2.08

550

5500

11000

4.0

3740

1060

9.1

420

920

1.29

6000

12000

4.4

4080

1460

10.7

450

lono

1.41

6500

13000

4.9

4400

1850

12.4

480

1060

1.55

7000

14000

5.4

4720

1250

14.2

500

1110

1.73

7500

15000

6.0

5010

2640

15.9

520

1140

1.93

8000

16000

6.6

5310

3030

17.7

530

1170

2.14

450

7500

10610

3.8

5480

2160

12.0

380

840

1.45

8000

11310

4.1

5830

2550

13.4

400

890

1.57

500

7500

10610

3.5

5420

1780

10.5

360

790

1.36

8000

11310

3.8

5750

2140

11.7

390

850

1.46

550

7500

10610

3.3

5340

1390

9.1

330

730

1.29

8000

11310

3.5

5710

1770

10.1

360

800

1.38

* MPI - Mean Point of Impact

4C—34—1 —1—(203—1)

Figure 6-21 (Sheet 1 of 4)

Change 6

6-68

T.O. 1F-4C-34-1-1

..”...... . . ....■W'llli.l.

dm JOSS RIPPLE RELEASE >W

MK20 MOD 2 & MOD 3 (ROCKEYE II)

2.0 G FULLOUT
0.10 SBC RELEASE INTERVAL
FUZE FUNCTION TINE - 7.0 SEC

■ DISTANCE mm

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

MPI* OF FIRST AND

LAST CLUSTER

VJRCS

PICKLE

"TM

CLUSTER

RELEASE

KNOTS

DIVE

ALT

SLANT

RELEASE

FUNCTION

BOMB

SETTING

TAS

ANGLE

AGL

RANGE

TIME

ALTITUDE

ANGLE

ALTITUDE

IMPACT

STICK

(DEG)

(FT)

(1000 FT)

(SEC)

(FT)

(DEG)

(FT)

(SBC)

(FT)

450

4000

11700

5.5

2860

1280

12.4

510

1110

1.35

4500

13160

6.4

3260

1860

15.3

500

1100

1.55

5000

14620

7.5

3680

2490

18.5

490

1070

1.81

5500

16080

8.7

4130

3190

21.9

470

1030

2.10

500

4000

11700

4.9

2800

940

10.7

520

1150

1.30

4500

13160

5.7

3170

1470

13.3

530

1170

1.47

5000

14620

6.7

3540

2030

16.1

530

1160

1.70

5500

16080

7.7

3940

2630

19.1

520

1150

1.96

6000

17540

8.8

4370

3270

22.1

510

1120

2.26

550

4000

11700

4.5

2740

650

9.3

520

1150

1.26

4500

13160

5.2

3100

1140

11.6

SSO

1200

1.39

5000

14620

6.0

3460

1640

14.1

560

1230

1.58

5500

16080

6.9

3820

2180

16.8

560

1230

1.82

6000

17540

7.9

4190

2750

19.5

560

1220

2.09

6500

19000

8.9

4600

3360

22.4

550

1210

2.39

450

5000

10000

4.2

3520

840

9.4

410

900

1.22

5500

11000

4.6

3900

1290

11.1

440

970

1.30

6000

12000

5.1

4260

1740

13.0

460

1010

1.42

6500

13000

5.7

4600

2190

15.0

470

1043

1.57

7000

14000

6.3

4950

2650

17.1

480

1060

1.74

7500

15000

6.9

5310

3130

19.2

490

1180

1.93

500

5500

11000

4.2

3840

930

9.6

430

940

1.26

6000

12000

4.6

4200

1360

11.3

460

1000

1.35

6500

13000

5.1

4540

1780

13.1

480

1060

1.47

7000

14000

5.6

4880

2220

15.0

500

1100

1.62

7500

15000

6.2

5210

2650

16.9

510

1120

1.79

8000

16000

6.8

5540

3090

18.8

520

1130

1.98

550

6000

12000

4.3

4120

1000

9.8

440

970

1.29

6500

13000

4.7

4470

1410

11.4

470

1040

1.38

7000

14000

5.1

4820

1830

13.2

500

1100

1.51

7500

15000

5.6

5150

2240

14.9

520

1140

1.66

8000

16000

6.2

5440

2650

16.7

530

1170

1.83

450

6500

9190

3.2

4780

790

8.6

320

700

1.19

7000

9990

3.4

5180

1210

9.8

340

750

1.24

7500

10610

3.7

5530

1600

11.0

370

820

1.30

8000

11310

3.9

5930

2020

12.4

390

870

1.39

500

7000

9900

3.2

5090

780

8.5

320

770

1.21

7500

10610

3.4

5480

1180

9.6

350

760

1.25

8000

11310

3.6

5860

1580

10.8

370

820

1.32

600

8000

11310

3.4

5780

1150

9.4

350

760

1.27

* MPI - Mean Point of Iirpact

4C—34— 1-1—(203- 2)

Figure 6-21 (Sheet 2 of 4)

Chang* 6

6-68A

T.O. 1F-4C-34-1-1

ME TOSS RIPPLE RELEASE

MK20 MOD 2 & MOD 3 (ROCKEYE II)

2.0 G PULLOUT
0.10 SEC RELEASE INTERVAL
FUZE FUNCTION TIME - 8.0 SEC

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE j

DISTANCE HTWeEn

MTI* OF FIRST AND

I AST CLUSTER

V.RCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

.MSI

ALT

AGE

(PT)

SLANT
RANGE
(1000 FT")

RELEASE

TITF.

fSECl

RELEASE

ALTITUDE

cm.

RELEASE

ANGLE

-MSI

CLUSTER

FUNCTION

ALTITUDE

-JED—

TIME

RELEASE

IMPACT

fSEC)

BOMB

STICK

_ cm

BOMB

STICK

_CFQ_

450

4000

11700

5.3

2890

4500

13160

6.1

3300

5000

14620

7.1

3700

5500

16080

8.3

4140

500

4500

13160

5.5

3200

5000

14620

6.3

3590

5500

16080

7.3

3980

6000

17540

8.4

4390

6500

19000

9.5

4840

550

4500

13160

5.0

3140

5000

14620

5.7

3510

5500

16080

6.5

3880

6000

17540

7.4

4250

6500

19000

8.4

4640

450

5500

11000

4.5

3930

6000

12000

4.9

4310

6500

13000

5.4

4670

7000

14000

6.0

5020

7500

15000

6.6

5380

8000

16000

7.2

5740

500

6000

12000

4.5

4230

6500

13000

4.9

4600

7000

14000

5.4

4940

7500

15000

5.9

5290

8000

16000

6.5

5620

550

6500

13000

4.5

4540

7000

14000

4.9

4900

7500

15000

5.4

5220

8000

16000

5.8

5580

450

7500

10610

3.6

5580

8000

11310

3.8

5980

500

8000

11310

3.5

5920

* H’l - Mean Foint of Impact

930

11.5

520

1140

1.25

1510

14.3

520

1140

1.39

2150

17.5

510

1110

1.59

2860

20.9

480

1060

1.84

1120

12.3

550

1190

1.34

1680

15.1

550

1200

1.51

2280

18.0

540

1180

1.72

2940

21.2

520

1140

1.98

3640

24.3

510

1220

2.26

770

10.7

560

1220

1.30

1280

13.1

570

1260

1.42

1820

15.7

570

1260

1.60

2400

18.5

570

1250

1.82

3010

21.3

560

1230

2.08

840

10.4

440

960

1.23

1310

12.1

460

1010

1.30

1770

14.0

500

1050

1.41

2245

16.1

490

1080

1.54

2730

18.2

500

1090

1.70

3230

20.3

500

non

1.87

900

10.5

450

990

1.27

1340

12.1

480

1050

1.34

1780

13.9

500

1090

1.45

2230

15.8

510

1130

1.58

2680

17.8

520

1150

1.73

950

10.6

460

1020

1.30

1370

12.2

490

1080

1.37

1740

13.9

510

1130

1.48

2230

15.7

530

1170

1.61

1020

10.2

360

790

1.23

1440

11.4

380

850

1.28

980

10.0

360

790

1.25

4C-34- l-l-( 203-3)

Change 6

6-68B

Figure 6-21 (Sheet 3 of 4)

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

MK20 MOD 2 & MOD 3 (ROCKEYE II)

4.0 G PULLOUT
0.10 AND 0.14 SECONDS
RELEASE INTERVAL

FUZE FUNCTION ALTITUDE - 2000 FT

PIC

KLECOND

ITIONS

FUZE

FUNCTION

TIME

SEC

MIDDLE BOMB OF EIGHT-BOMB RIPPLE

TAS

KTS

DIVE

ANG

DEG

ALT

AGL

PICKLE

RELEASE

TIME

SEC

EIGHT

BOMB

STICK

LENGTH

SETTING

ALT

ANG

DEG

RELEASE

IMPACT

SEC

0.10 SEC RELEASE INTERVAL

500

550

8000

8.0

7.3

2.40

2.30

6620

6530

-36

-37

13.3

114

1010

960

1.40

1.41

0.14 SEC RELEASE INTERVAL

500

550

8000

8.0

7.2

2.52

2.38

6550

6480

-35

-37

13.3

12.4

1420

1330

1.40

1.41

4C—34— 1 — 1 —(20 3—4)

Figure 6-21 (Sheet 4 of 4)

Change 6

6-68C

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE 2%

CBU-24B/B, -29B/B, -49B/B

2.0 G PUI.LOJT
0.06 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTA
MPI* C
LAI

NCI; Bl
)F FIRI

;t cut

TWEEN
!T AND
TER

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

cnr.ro

ALT

AGL

(FT)

SLANT
RANGE
C1000 FT)

PICKLE

RELEASE

TIME

(SFC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)..

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

JU1

BOMB

STICK

(FT)

BOMB

STICK

(FT)

500

5130

6.38

3700

- 8

7.6

16.6

290

360

730

1.44

6840

7.64

5271

- 6

12.4

20.0

350

430

860

1.24

550

5130

6.18

3550

-10

6.6

15.9

280

350

690

1.61

6840

7.34

5090

- 8

11.2

19.1

340

430

850

1.34

600

5130

6.12

3390

-11

5.8

15.2

260

320

650

1.83

6840

7.10

4920

- 9

10.2

18.4

330

410

830

1.46

500

5000

4.56

3210

-22

3.6

11.6

150

190

370

1.82

7500

5.40

5440

-20

8.5

15.2

220

280

590

1.29

10000

6.66

7560

-17

12.8

18.8

290

370

730

1.23

550

5000

4.50

3040

-23

3.0

11.0

130

170

330

2.12

7500

5.22

5270

-21

7>7

14.5

230

280

560

1.39

10000

6.42

7360

-19

11.8

17.9

280

350

710

1.31

600

7500

5.16

5090

-22

7.0

13.9

210

260

530

1.51

10000

6.30

7150

-20

11.1

17.3

270

340

680

1.39

500

10610

4.26

8100

-37

9.5

14.3

200

250

510

1.21

14140

5.28

11080

-34

13.7

18.2

250

320

630

1.23

550

10610

4.14

7920

-38

8.9

13.6

190

240

480

1.28

14140

5.16

10840

-36

12.9

17.5

240

300

600

1.31

600

10610

4.08

7730

-38

8.3

13.1

180

230

450

1.35

14140

5.04

10635

-36

12.3

16.8

230

290

570

1.37

* MPI - Mean Point of Impact

4C—34—1—1—(208-1)

6-88D

Chang* 6

Figure 6-21A (Sheet 1 of 9)

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

CBU-24B/B, -29B/B, -49B/B

2.0 G PULLOUT
0.10 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE. CONDITIONS

—---

MIDDLE BCMB IN RIPPLE RELEASE

DISTANCE BETWEEN
MPI* OF FIRST AND
LAST CLUSTER

WRCS

C B

SETTING

KNOTS DIVE ALT

TAS ANGLE AGL

(DEG1 (FT)

PICKETT

RELEASE

TIME

(SECT

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

PEG)

CLUSTER

FUNCTION

TIME

(SEC)

"TIME'

RELEASE

IMPACT

(SEC)

BCMB

STICK

..ffT)

BOMB

STICK

JHI

BOMB

STICK

(FT)

500

5130

6.40

3700

6840

7.70

5270

550

5130

6.20

3540

6840

7.30

5090

600

5130

6.10

3390

6840

7.10

4920

500

5000

4.50

3230

7500

5.40

5440

10000

6.70

7560

550

5000

4.50

3040

7500

5.30

5240

10000

6.40

7370

600

7500

5.10

5110

10000

6.30

7150

500

10610

4.30

8080

14140

5.30

11070

550

10610

4.10

7940

14140

5.10

10870

600

10610

4.10

7710

14140

5.00

10660

- 8

7.6

16.6

480

600

1210

1.44

- 6

12.4

20.1

580

720

1440

1.24

-10

6.6

15.9

460

580

1150

1.62

- 8

11.2

19.1

570

710

1430

1.34

-11

5.8

15.2

430

540

1080

1.84

- 9

10.2

18.4

550

690

1380

1.46

-22

3.6

11.5

250

310

620

1.80

-20

8.4

15.2

400

490

990

1.29

-17

12.8

18.8

490

610

1220

1.23

-23

3.0

10.9

220

280

550

2.12

-21

7.6

14.5

370

470

940

1.40

-19

11.8

18.0

470

590

1180

1.31

-22

7.0

13.9

350

440

880

1.51

-20

11.1

17.3

450

560

1130

1.39

-37

9.5

14.3

340

420

850

1.21

-34

13.7

18.2

420

530

1050

1.23

-38

8.9

13.6

320

400

800

1.28

-36

12.9

17.5

400

500

1000

1.31

-38

8.3

13.1

300

380

750

1.35

-36

12.3

16.8

380

480

960

1.37

* MPI - Mean Point Of Impact

4C-34-1-

1—(208 - 2)

Figure 6-21A (Sheet 2 of 9)

Change 6

6-68E

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

CBU-24B/B, -29B/B, -49B/B

2.0 G PULLOUT
0.14 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIFFLF. RELEASE

DISTANCE BI
MTI* OF FIR5
LAST CUE

3TWEFN
5T AND
ITER

'ARCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

FICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

PEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SF-C)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

500

5130

6.44

3690

- 8

7.6

16.6

680

850

1700

1.44

6840

7.70

5260

- 6

12.4

20.1

810

1010

2020

1.24

550

5130

6.16

3550

-10

6.6

15.8

640

810

1610

1.62

6840

7.28

5090

- 8

11.2

19.1

790

1000

1990

1.34

600

5130

6.16

3370

-11

5.8

15.2

610

750

1520

1.84

6840

7.14

4910

- 9

10.3

18.4

770

960

1930

1.46

500

5000

4.62

3190

-22

3.6

11.5

350

430

870

1.83

7500

5.46

5420

-20

8.4

15.2

550

690

1380

1.29

10000

6.72

7550

-17

12.8

18.8

680

850

1710

1.23

550

5000

4.48

3040

-23

3.0

10.9

310

380

770

2.12

7500

5.32

5230

-21

7.6

14.5

520

650

1310

1.40

10000

6.44

7350

-19

11.8

18.0

660

830

1650

1.31

600

7500

5.18

5073

-22

6.9

13.9

490

620

1230

1.51

10000

6.30

7150

-20

11.1

17.3

630

790

1580

1.39

500

10610

4.34

8050

-37

9.5

14.3

470

590

1180

1.21

14140

S.32

11060

-34

13.7

18.2

590

740

1470

1.23

550

10610

4.20

7880

-38

8.8

13.6

450

560

1110

1.29

14140

5.18

10820

-36

12.9

17.4

560

700

1400

1.31

600

10610

4.06

7740

-38

8.3

13.1

420

520

1050

1.35

14140

5.04

10630

-36

12.3

16.8

530

670

1330

1.37

* MPI - Mean Point of Impact

Figure 6-21A (Sheet 3 of 9)

4C-34-1-M 208 -3)

6-68F

Change 6

T.O. 1F-4C-34-1-1

VIVE TOSS RIPPLE RELEASE

CBU-24B/B, -29B/B, -49B/B

3.0 G PULLOUT
0.06 SRC RELEASE INTERVAL
HOB - 1800 FT ACL

PICKLE

CONDITIONS

ITDDLF. BCM IN

RIPPLE REIEASE

DISTANCE BETWEEN
MPI* OF FIRST AND
1AST CLUSTER

NRCS

C B

SETTING

KNOTS

TAS

PTVF. ALT
ANGLE ACL
(DEG) (FT)

SLANT
PANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE.

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

RE I EASE
TO

IMPACT

(SEC)

BOTH

STICK

(FT)

BOMB

STICK

(FT)

—

BOMB

STICK

(FT)

500

3420

3.96

2540

- 7

4.1

14.9

360

450

900

2.09

5130

4.38

4210

- 6

10.0

18.5

490

610

1210

1.30

6840

5.28

5870

- 2

15.4

22.8

540

680

1360

1.19

550

3420

4.02

2410

- 8

3.2

14.3

320

400

800

2.58

5130

4.26

4090

- 7

8.9

12.7

470

590

1180

1.42

6840

5.10

5730

- 4

14.1

21.6

550

690

1370

1.27

600

3420

4.14

2280

- 9

2.4

13.8

270

350

690

3.35

5130

4.20

3980

- 9

8.1

17.1

460

570

1140

1.56

6840

4.98

5590

- 6

13.1

20.8

540

680

1350

1.38

500

5000

3.18

3780

-21

5.1

12.8

270

340

670

1.53

7500

3.84

6090

-18

10.3

16.8

390

490

980

1.23

10000

4.68

8380

-14

15.2

21.0

470

590

1170

1.19

550

5000

3.12

3661

-22

4.5

12.2

250

310

620

1.69

7500

3.72

5960

-19

9.4

16.1

370

470

930

1.32

10000

4.56

8220

-16

14.2

20.1

460

570

1140

1.28

600

5000

3.12

3530

-22

3.9

11.7

240

290

570

1.90

7500

3.66

5830

-20

8.7

15.4

360

450

890

1.42

10000

4.44

8060

-17

13.3

19.3

440

550

1090

1.36

500

5300

7.5

2.28

3950

-39

3.5

9.0

170

210

420

1.45

7070

2.52

5590

-38

6.1

11.2

230

280

570

1.25

10610

3.12

8800

-35

10.8

15.5

330

410

820

1.19

14140

3.78

12010

-32

15.4

19.9

400

500

1000

1.21

550

7070

2.46

5480

-39

5.5

10.6

210

270

530

1.33

10610

3.06

8650

-36

10.1

14.8

310

390

770

1.26

14140

3.72

11820

-34

14.6

19.1

380

480

960

1.29

600

7070

2.40

5370

-40

5.1

10.1

200

240

490

1.42

10610

3.00

8510

-37

9.5

14.3

290

360

730

1.33

14140

3.66

11640

-35

13.9

18.4

360

450

910

1.37

* f<PT - Mean Point of Impact

4C-34 —V

Figure 6-21A (Sheet 4 of 9)

Change 6

l-< 208 -4)

6-68G

T.O. 1F-4C-34-1-1

Dm TOSS RIPPLE RELEASE

CBU-24B/B, -29B/B, -49B/B

3.0 o pullout

0.10 SEC PELEASE INTERVAL
HOB - 1800 FT ACL

FICKLE CCNPITICNS

MIPDLE BOMB IN RIPPLF RELEASE

PI STANCE BT
MPI* OF FIR!
LAST CLU!

^TWEEN
5T ANP
5TEP

WRCS

C B

SETTING

KNOTS PIVE ALT
TAS ANCLE ACL
(PEC) (FT)

SLANT
RANGE
(1000 FT)

PlCKlE

REIEASF.

TOT

(SEC)

RELEASE

ALTIHIPE

(FT)

RELEASE

ANGLE

(DEC)

CLUSTER
FUNCTION
TOT
(SEC) .

TOT

RELEASF

IMPACT

(SEC)

BOMB

STICK

JZI1

BOMB

STICK

_£DJ

BOMB

STICK

_£HL

500 20 3420

4.10

2520

- 7

4.1

15.0

610

770

1530

2.10

5130

4.40

4200

- 6

10.0

18.5

810

1020

2020

1.30

6840

5.30

5860

- 2

15.3

22.5

910

1130

2250

1.19

550 20 3420

4.10

2400

- 8

3.2

14.3

540

680

1350

2.61

5130

4.30

4080

- 7

8.9

17.7

790

990

1980

1.42

6840

5.10

5720

- 4

14.0

21.5

910

1140

2270

1.28

600 20 5130

4.20

3970

- 9

8.1

17.0

760

950

1890

1.57

6840

5.00

5580

- 6

13.0

20.7

900

1130

2240

1.38

500 30 5000

3.20

3770

-20

5.1

12.9

450

570

1130

1.53

7500

3.80

6100

-18

10.3

16.8

650

820

1630

1.23

10000

4.70

8380

-14

15.2

21.0

780

980

1950

1.19

550 30 5000

3.10

3670

-22

4.5

12.1

410

520

1030

1.69

7500

3.70

5970

-19

9.4

16.0

620

780

1550

1.32

10000

4.50

8230

-16

14.1

20.0

760

950

1890

1.28

600 30 5000

3.10

3540

-22

3.9

11.7

380

480

950

1.90

7500

3.70

5810

-20

8.7

15.5

590

740

1480

1.42

10000

4.50

8040

-17

13.4

19.4

730

920

1830

1.36

500 45 5300

7.5

2.30

3940

-39

3.5

9.0

280

350

690

1.45

7070

2.50

5600

-38

6.1

11.2

380

470

950

1.25

10610

3.10

8810

-35

10.8

15.5

540

680

1360

1.19

14140

3.80

12000

-32

15.4

19.9

670

840

1670

1.21

550 45 7070

2.50

5450

-39

5.5

10.6

350

440

880

1.33

10610

3.10

8630

-36

10.1

14.8

510

640

1280 1.26

14140

3.70

11830

-34

14.6

19.0

640

800

1590 1.29

600 45 7070 10

2.40

5370

-40

5.1

10.1

330 410

820 1.42

10610 15

3.00

8510

-37

9.5

14.3

480 600

1210 1.33

14140

3.70

11610

-35

13.9

18.4

610 760 1520 1.37

* MPT - ffean Point of Iirmact

4C—34—1—1—(208 —5)

Figure 6-21A (Sheet 5 of 9)

6-68H

Change 6

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

ifv

CBU-24B/B, -29B/B, -49B/B

3.0 G PULI CUT
0.14 SEC RELEASE INTERVAL
HOB - 1R00 FT ACL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLF RELEASE

“niSTANCE BETWEEN

MPI* OF FIRST AND
LAST CLUSTER

WRCS

SETTING

KNOTS

TAS

DIVE ALT
ANGIE Aa
(DEC) (FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIM-

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEC)

CLUSTER

FUNCTION

TIME

(SEC)

Tift

RELEASE

IITACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

500

3420

4.06

2520

- 7

4.1

15.0

850

1080

2130

2.10

5130

4.48

4190

- 5

10.0

18.6

1140

1440

2850

1.30

6840

5.32

5860

- 2

15.3

22.6

1260

1580

3150

1.19

550

3420

4.06

2400

- 8

3.2

14.3

740

940

1870

2.62

5130

4.34

4080

- 7

9.0

17.8

1110

1400

2780

1.42

6840

5.18

5710

- 4

14.1

21.6

1280

1610

3191

1.28

600

5130

4.20

3970

- 9

8.1

17.0

1060

1330

2640

1.57

6840

5.04

5570

- 6

13.1

20.8

1250

1580

3140

1.38

500

5000

3.22

3760

-20

5.1

12.8

620

790

1570

1.53

7500

3.92

6060

-17

10.3

16.9

920

1150

2290

1.23

10000

4.76

8360

-14

15.2

21.1

1040

1370

2730

1.19

550

5000

3.22

3620

-21

4.4

12.2

580

730

1450

1.70

7500

3.78

5940

-19

9.4

16.1

870

1100

2180

1.32

10000

4.62

8190

-16

14.2

20.1

1070

1340

2660

1.28

600

5000

3.08

3540

-23

3.9

11.6

530

660

1320

1.91

7500

3.64

5830

-20

8.7

15.4

820

1030

2060

1.42

10000

4.48

8040

-17

13.3

19.3

1020

1280

2550

1.36

500

5300

7.5

2.24

3970

-39

3.6

9.0

390

480

940

1.46

7070

2.52

5590

-38

6.0

11.2

530

660

1320

1.25

10610

3.08

8820

-37

10.8

15.5

760

950

1900

1.19

14140

3.78

12000

-33

15.4

19.8

930

1170

2110

1.21

550

7070

2.52

5440

-39

5.5

10.6

490

620

1220

1.34

10610

3.08

8640

-36

10.1

14.8

720

900

1790

1.26

14140

3.78

11780

-34

14.6

19.1

890

1120

2230

1.29

600

7070

2.38

5380

-40

5.1

10.1

460

570

1130

1.43

10610

3.08

8460

-37

9.5

14.2

680

850

1690

1.34

14140

3.64

11650

-35

13.9

18.4

850

1060

2120

1.37

* tV T - *'oan Point of Ttract

4C-34-1-

Figure 6-21A (Sheet 6 of 9)

Change 6

1—<208 -6)

6-68J

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

CBU-24B/B, -29B/B, -49B/B

4.0 G PULLOUT
0.06 SF.C RF.LFASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

IT DOLE BOf® IN RIPPLE PELFASF. j

DIST/
MPT* 0
LA5

\N'CE Bf
)F FIP(

;t cut;

•TV.TEN

;t and

STEP

WRCS

C B

SETTING

KNOTS DIVE ALT
TAS ANCLE AGL
(ISO (PH

SLANT
RANGE
(1000 FT)

PTtfcnq

REIEASE

(SEC)

RELEASE

altitude

(FT)

RELEASE

ANGLE

(DEC)

CLUSTER

FUNCTION

TIME

(SEC)

TIM]-.

RELEASE

impact

(SEC)

BOf®

STICK

(FT)

BOf®

STICK

(FT)

BOf®

STICK 1

(FT)

500

3420

5130

6840

3.12

3.48

4.26

2730

4410

6100

- 7

- 4
+ 1

5.1

11.0

17.0

15.6

10.4

24.0

S30

660

720

670

830

900

1320

1650

1790

1.82

1.26

1.17

550

3420

5130

6840

3.12

3.42

4.02

2640

4310

5980

- 8
- 6
- 2

4.3

10.0

15.3

15.0

18.6

22.6

490

660

740

610

830

920

1220

1650

1840

2.14

1.36

1.25

600

3420

5130

6840

3.18

3.36

3.06

2540

4220

5870

- 8

- 7

- 4

3.6

0.2

14.4

14.5

17.0

21.9

450

640

730

560

810

910

1120

1590

1820

2.55

1.49

1.35

500

5000

7500

10000

2.64

3.12

3.78

30 00
6370
8590

-20
-16
- 6

5.8

11.2

16.5

13.4

17.6

22.2

300

540

630

480

680

790

960

1350

1580

1.45

1.21

1.18

550

5000

7500

10000

2.58

3.00

3.66

3901

6270

8590

-21

-18

-14

5.1

10.2

15.3

12.8

16.8

21.2

360

510

620

450

650

780

890

1290

1560

1.59

1.29

1.26

600

5000

7500

10000

2.52

3.00

3.60

3820

6140

8460

-22

-10

-16

4.6

9.6
14.5

12.2

16.2

20.4

330

400

600

410

620

750

820

1230

1500

1.75

1.39

1.35

500

5300

7070

10610

14140

7.5

1.02

2.16

2.58

3.12

4170

5810

9130

12410

-39

-37

-35

-31

3.0

6.5

11.4

16.3

9.3

11.6

16.1

20.7

230

320

450

550

290

400

560

680

560

780

1120

1370

1.40

1.24

1.18

1.20

550

5300

7070

10610

14140

7.5

1.92

2.10

2.52

3.06

4060

5720

9010

12250

-40

-38

-36

-33

3.5

5.9

10.7

15.4

8.8

11.0

15.4

19.9

210

300

420

520

260

370

530

650

510

720

1060

1310

1.51

1.31

1.25

1.28

600

7070

10610

14140

2.04

2.52

3.00

5630

8860

12110

-39

-37

-34

5.5

10.1

14.7

10.5

14.8

19.2

270

400

500

340

500

620

670

1000

1240

1.39

1.33

1.36

* ><PI - ftean Point of Impact

40-34—1-1—(208-7)

Figure 6-21A (Sheet 7 of 9)

6-68K

Change 6

T.O. 1F-4C-34-1-1

dlVE TOSS RIPPLE RELEASE

CBU-24B/B, -29B/B, -49B/B

4.0 R PUIXOPT
0.10 SEC RELEASE INTERVAL
HOB - 1800 FT ARE

PICKLE

CONDITIONS

MIDDLE BOMB IN

RIPPLE RELEASE

CT)TSW(T:' between

MPI* OF FIRST AND
LAST OUSTER

WRCS

C B

SFTTINR

KNOTS

TAS

T)I\T

ANRI.F

(DEC)

ALT

ACL

JEQ.

SIANT
PAN RE
(1000 FT

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANRIE

(PER)

CLUSTER

FUNCTION

TIME

(SEC)

TTMF

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

500

3420

3.10

2730

- 7

5.1

15.5

870

1110

2180

1.82

5130

3.50

4410

- 4

11.1

19.4

1110

1390

2770

1.26

6840

4.20

6100

16.8

23.8

1190

1490

2070

1.17

550

3420

3.10

2640

- 8

4.2

14.0

800

1020

2020

2.14

5130

3.40

4310

- 6

10.0

18.6

1090

1380

2730

1.37

6840

4.00

5080

- 3

15.3

22.6

1220

1540

3080

1.25

600

3420

3.20

2530

- 8

3.6

14.5

750

950

1880

2.55

5130

3.30

4230

- 8

0.0

17.8

1040

1320

2600

1.50

6840

4.00

5870

- 4

14.4

22.0

1220

1540

3050

1.35

500

5000

2.60

4000

-20

5.7

13.3

640

800

1590

1.45

7500

3.20

6340

-16

11.2

17.7

010

1140

2260

1.21

10000

3.80

8720

-12

16.4

22.2

1050

1320

2630

1.18

550

5000

2.60

3800

-21

5.1

12.7

500

750

1490

1.59

7500

3.00

6260

-18

10.2

16.7

860

1080

2140

1.29

10000

3.70

8580

-14

15.3

21.2

1040

1300

2590

1.26

600

5000

2.60

3780

-22

4.6

12.2

550

600

1380

1.76

7500

3.00

6140

-10

9.5

16.2

820

1030

2040

1.39

10000

3.60

8450

-16

14.4

20.3

1000

1250

2490

1.35

500

5300

7.5

1.00

4180

-39

3.0

9.3

370

470

900

1.40

7070

2.10

5840

-38

6.5

11.6

520

650

1270

1.23

10610

2.60

9120

-35

11.4

16.1

750

940

1860

1.18

14140

3.10

12420

-31

16.3

20.7

910

1140

2270

1.20

550

5300

7.5

1.00

4070

-40

3.5

8.8

340

430

830

1.50

7070

2.10

5720

-38

5.9

11.0

490

610

1180

1.31

10610

2.50

0020

-36

10.7

15.4

700

880

1760

1.25

14140

3.00

12280

-33

15.4

10.8

870

1000

2170

1.28

600

7070

2.10

5500

-30

5.5

10.5

450

570

1100

1.40

10610

2.50

8870

-37

10.1

14.8

660

830

1660

1.33

14140

3.00

12110

-34

14.7

19.2

830

1040

2070

1.36

* »TT - Mean Point of Impact

4C-34-1

Figure 6-21A (Sheet 8 of 9)

Change 6

1—(208—8)

6-68L

T.O. 1F-4C-34-1-1

Dm TOSS RIPPLE RELEASE

CBU-24B/B, -29B/B, -49B/B

4.0 G PULLOUT
0.14 SF.O RELEASE TNTEFVAL
HOB - 1800 FT AGL

PICKLF CONDITIONS

MIDDLE BOf® TN P.IPPLF. PFLF.ASF.

DISTANCE BETWEEN
MPI* OF FIDST AND
LAST CLUSTFP

KNOTS OUT- ALT
TAS ANGLF A GI.
(T)F.(T) (FT)

SI ANT
PANOF
(1000 FT)

PICKLF

RFTFASF.

TIL'S

(SFC)

RELFASF

ALTITUDE

(FT)

PEI .EASE
ANGLF
(DEG)

OLUSTF.P

FUNCTION

TIUF

TIME

PFIFASF

Tf’PACT

(SF.C)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

WPCS

C B

SETTING

500 20

550 20

600 20

500 30

550 30

600 30

500 45

550 45

600 45

3420

3.22

2710

- 6

5.2

15.7

1260

1610

3180

1.83

5130

3.50

4400

- 4

11.0

19.4

1540

1050

3840

1.26

6840

4.20

6090

16.7

23.7

1650

2080

4140

1.17

3420

3.22

2620

- 7

4.3

15.1

1160

1490

2950

2.15

5130

3.36

4310

- 7

9.8

18.4

1510

1910

3770

1.37

6840

4.06

5970

- 2

15.3

22.6

1710

2160

4280

1.25

3420

3.22

2520

- 8

3.6

14.5

1040

1330

2640

2.57

5130

3.36

4210

- 8

9.1

17.9

1470

1860

3670

1.50

6840

3.92

5860

- 5

14.2

21.7

1680

2120

4200

1.36

5000

2.66

3980

-20

5.8

13.4

890

1130

2250

1.45

7500

3.08

6370

-17

11.1

17.5

1240

1570

3170

1.21

10000

3.78

8720

-12

16.4

22.1

1470

1850

3670

1.18

5000

2.52

3920

-21

5.1

12.6

820

1040

2050

1.59

7500

3.08

6240

-18

10.3

16.8

1210

1520

3020

1.29

10000

3.64

8590

-15

15.2

21.1

1440

1810

3590

1.26

5000

2.52

3810

-22

4.6

12.2

760

960

1900

1.76

7500

2.94

6160

-20

9.5

16.1

1130

1430

2840

1.39

10000

3.64

8440

-16

14.4

20.4

1400

1760

3490

1.35

5300

7.5

1.96

4150

-39

3.9

9.3

520

650

1240

1.41

7070

2.10

5840

-38

6.5

11.6

720

910

1730

1.23

10610

2.66

9090

-34

11.4

16.2

1040

1310

2610

1.18

14140

3.08

12420

-31

16.2

20.6

1270

1590

3170

1.20

5300

7.5

1.96

40 30

-39

3.4

8.8

470

600

1140

1.51

7070

2.10

5720

-39

5.9

11.0

670

840

1610

1.31

10610

2.52

9010

-36

10.7

15.4

980

1230

2440

1.25

14140

3.08

12240

-33

15.4

19.9

1220

1530

3040

1.28

7070

2.10

5590

-39

5.4

10.5

620

790

1500

1.40

10610

2.52

8860

-37

10.1

14.8

930

1160

2300

1.33

14140

3.08

12060

-34

14.7

19.2

1160

1450

2900

1.36

♦ »f>T - Mean Point of Impact

4C-34-1-M 208-9)

Figure 6-21A (Sheet 9 of 9)

6-68M

Change 6

T.O. 1F-4C-34-1-1

dm TOSS RIPPLE RELEASE Hg

CBU-52A/B

2.0 G PULLOUT
0.06 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKL]

F. COND

[TITOS

MIDDLE BTO® IN RIPPLE. RELEASE

"DISTANCE BET!,£fe>:
MPI* OF FIRST AND
LAST CLUSTER

_(£_

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

imwaai

|§

RELEASE

ALTITUDE

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

THE

(SEC)

“TOE

RELEASE

HTACT

(SEC)

BOMB

STICK

(PT)

BTO®

STICK

(FT)

BOMB

STICK

(FT)

SOO

5130

6.32

3705

- 9

7.6

16.0

290

360

730

1.39

6840

7.64

5270

- 6

12.4

19.5

350

430

860

1.22

SS0

5130

6.08

3560

-10

6.6

15.2

280

350

690

1.55

6840

7.28

5090

- 8

11.2

18.6

340

430

850

1.32

600

5130

5.96

3410

-11

5.8

14.6

260

330

650

1.74

6840

7.10

4920

- 9

10.3

17.8

330

410

830

1.43

SOO

5000

4.38

3270

-22

3.7

11.0

150

190

380

1.65

7500

5.34

5460

-20

8.5

14.7

240

300

600

1.26

10000

6.66

7560

-17

12.8

18.3

290

370

730

1.22

550

5000

4.32

3110

-23

3.1

10.4

140

170

350

1.88

7500

5.16

5300

-21

7.7

14.0

200

280

570

1.35

10000

6.42

7360

-19

11.9

17.5

280

350

710

1.30

600

7500

5.04

5130

-22

7.0

13.4

210

260

530

1.46

10000

6.30

7150

-20

11.1

16.8

270

340

680

1.38

500

10610

4.26

8100

-37

9.6

13.9

200

260

510

1.20

14140

5.28

11080

-34

13.8

17.9

250

320

630

1.23

550

10610

4.14

7920

-38

8.9

13.3

190

240

480

1.27

14140

5.16

10840

-36

13.0

17.2

240

300

600

1.31

600

10610

4.08

7730

-38

8.3

12.7

180

230

440

1.34

14140

5.04

10640

-36

12.3

16.5

230

290

570

1.38

*MPI - Mean Point of Inpact

4C—34— 1— 1—(207 — 1)

Figure 6-21B (Sheet 1 of 9)

Change 6

6-6 8N

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

CBU-52A/B

2.0 G PULLOUT
0.10 SEC RELEASE INTERVAL
liOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE l!OMB IK

RIPPLE RELEASE

"DISTATFBI

MPI* OF FI95
LAST CLU5

TMTn
IT AND
iTER

fra

KNOTS

TAS

DIVE

ANGLE

(DEC!

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

altitude:

(ET)

RELEASE
ANGLE
(HEG) _

CLUSTER

FUNCTION

TIFT,

(SEC)

THE

RELEASE

IMPACT

(SEC)

BCMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

500

5130

6.30

3710

- 9

7.6

16.0

480

600

1210

1.39

6840

7.60

5270

- 6

12.4

19.5

570

720

1440

1.22

550

5130

6.10

3560

-10

6.6

15.3

460

580

1150

1.55

6840

7.30

5090

- 8

11.2

18.6

570

710

1420

1.32

600

5130

6.00

3400

-11

5.8

14.6

430

540

980

1.74

6840

7.10

4920

- 9

10.3

17.8

550

690

1380

1.43

500

5000

4.40

3260

-22

3.7

11.0

260

320

640

1.66

7500

5.40

5440

-20

8.5

14.7

400

500

1000

1.26

10000

6.60

7590

-18

12.8

18.3

490

610

1220

1.22

550

5000

4.30

3120

-23

3.1

10.4

230

290

5S0

1.88

7500

5.20

5280

-21

7.7

13.9

380

470

940

1.36

10000

6.40

7370

-19

11.9

17.5

470

590

1180

1.30

600

7500

5.10

5110

-22

7.0

13.4

350

440

890

1.46

10000

6.30

7154

-20

11.1

16.8

450

570

1130

1.38

500

10610

4.30

8080

-37

9.5

13.9

340

420

850

1.20

14140

5.30

11070

-34

13.8

17.9

420

530

1060

1.23

550

10610

4.10

7940

-38

8.9

13.3

320

400

800

1.27

14140

5.10

10870

-36

13.0

17.2

400

500

1000

1.31

600

10610

4.00

7780

-39

8.4

12.8

300

380

760

1.34

14140

5.10

10600

-36

12.3

16.5

380

480

960

1.38

*MPI - Mean Point of Inpact

Figure 6-21B (Sheet 2 of 9)

4C-34-l-l-( 207-2)

Change 6

6-68P

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

CBU-52A/B

2.0 G PULLOUT
0.14 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

FICKLE CONDITIONS^

MIDDL1; BOMB IN

RIPPLE RELEASE

riisTAVcf-'

MPI* OF FIRST AND
LAST CLUSTER

1VRCS

KNOTS DIVE ALT
TAS ANGLE AGL
(DEG) (FD

SLANT

raw:

(1000 FT)

PICKLE

RELEASE

TEE

(SEC)

RELEASE

ALTITUDE

_CEO_

RELEASE

AICLE

_(S!2SI_

CLUSTER

FUNCTION

TEE

_[SEQ_

TnE

RELEASE

INTACT

ROME

STICK

Ed.®

STICK

.sm

BC1J!

STICK

_ara

C E

SETTING

500

5130

6.30

3710

- 9

7.6

16.0

680

850

1690

1.39

6840

7.56

5280

- 6

12.4

19.4

800

1010

2010

1.22

SSO

5130

6.16

3550

-10

6.6

15.3

650

810

1620

1.55

6840

7.28

5090

- 8

11.2

18.5

790

1000

1990

1.32

600

5130

6.02

3400

-11

5.8

14.6

610

760

1520

1.74

6840

7.28

4890

- 9

10.3

17.9

780

970

1950

1.43

500

5000

4.48

3230

-22

3.6

11.0

360

450

890

1.67

7500

5.32

5460

-20

8.5

14.6

550

690

1390

1.26

10000

6.72

7550

-17

12.8

18.4

690

850

1710

1.22

550

5000

4.34

3100

-23

3.1

10.4

320

400

800

1.89

7500

5.18

5280

-21

7.7

13.9

530

660

1320

1.36

10000

6.44

7350

-19

11.9

17.5

660

820

1650

1.30

600

7500

5.04

5130

-22

7.0

13.4

500

620

1240

1.45

10000

6.30

7150

-20

11.1

16.8

630

790

1580

1.38

500

10610

4.20

8130

-37

9.6

13.9

480

590

1190

1.20

14140

5.32

11060

-34

13.7

17.9

590

740

1480

1.23

550

10610

4.20

7880

-38

8.8

13.2

450

560

1120

1.27

14140

5.18

10820

-36

12.9

17.1

560

700

1400

1.31

600

10610

4.06

7740

-38

8.3

12.7

420

530

1060

1.34

14140

5.04

10630

-36

12.3

16.5

540

670

1340

1.38

*MPI - lean Point of Impact

Figure 6-2IB (Sheet 3 of 9)

4C-34-l-l-(207- 3)

Change 6

6-68Q

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

CBU-52A/B

3.0 G PULLOUT
0.06 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BI
MPI* OF FIR!
_LAST CLU!

TWEEN
5T AND
pR

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

pTlkEe

RELEASI

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASI

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

500

3420

3.90

2540

-8

4.0

14.3

360

450

880

1.97

5130

4.38

4200

-6

9.9

17.9

480

610

1210

1.28

6840

5.34

5860

-2

15.4

22.1

540

680

1350

1.18

550

3420

3.96

2420

-9

3.2

13.7

320

400

790

2.40

5130

4.26

4090

-7

8.9

17.1

470

590

1180

1.39

6840

5.10

5720

-4

14.0

21.0

540

680

1360

1.27

600

3420

4.02

2290

-9

2.4

13.2

270

340

680

3.02

5130

4.14

3980

-9

8.0

16.4

460

570

1130

1.52

6840

4.98

5580

-6

13.0

20.2

540

670

1340

1.37

500

5000

3.12

3790

-21

5.1

12.2

270

340

680

1.44

7500

3.84

6090

-18

10.3

16.3

390

490

980

1.21

10000

4.68

8380

-14

15.2

20.6

470

590

1170

1.19

550

5000

3.06

3680

-22

4.5

11.6

250

320

630

1.58

7500

3.72

5960

-19

9.4

15.6

380

470

940

1.30

10000

4.50

8230

-16

14.2

19.6

450

570

1140

1.27

600

5000

3.00

3580

-23

4.0

11.1

230

290

570

1.76

7500

3.60

5850

-21

8.7

14.9

360

450

890

1.39

10000

4.44

8060

-17

13.4

18.9

440

550

1090

1.36

500

5300

7.5

2.22

3990

-39

3.6

8.6

170

210

430

1.37

7070

2.52

5590

-38

6.1

10.8

230

290

570

1.22

10610

3.12

8800

-35

10.8

15.2

300

410

820

1.18

14140

3.78

12010

-32

15.5

19.5

400

500

1010

1.21

550

7070

2.40

5510

-39

5.6

10.2

220

270

540

1.29

10610

3.06

8650

-36

10.1

14.5

210

390

770

1.25

14140

3.72

11290

-30

14.6

18.8

380

480

960

1.29

600

7070

2.40

5370

-40

5.1

9.7

200

250

500

1.37

10610

3.00

8510

-37

9.6

13.9

290

370

730

1.33

14140

20 -a

3.66

11640

-35

14.0

18.1

370

460

910

1.37

* MPI - Mean Point of Impact

4C—34—1—1—(207-4)

Figure 6-21B (Sheet 4 of 9)

6-68R

Change 6

T.O. 1F-4C-34-1-1

VIVE TOSS RIPPLE RELEASE

CBU-52A/B

3.0 G PULLOUT
0.10 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI* OF FIRST AND
LAST CLUSTER

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG}

ALT

AGL

IED.

SLANT
RANGE
(1000 FT}

PICKLE

RELEASE

TIME

(SEC}

RELEASE

ALTITUDE

(FT}

RELEASE

ANGLE

(DEG}

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

I2Q_

BO®

STICK

(FT)

BO®

STICK

(FT)

500

3420

3.90

2540

5130

4.40

4200

6840

5.30

5860

550

3420

3.90

2430

5130

4.20

4100

6840

5.10

5720

600

3420

4.00

2300

5130

4.20

3970

6840

5.00

5580

500

5000

3.10

3800

7500

3.80

6100

10000

4.70

3830

550

5000

3.10

3670

7500

3.70

5970

10000

4.50

8230

600

5000

3.00

3580

7500

3.60

5850

10000

4.40

8080

500

5300

7.5

2.20

4000

7070

2.50

5600

10610

3.10

8810

14140

3.80

12000

550

7070

2.40

5510

10610

3.10

8630

14140

3.70

11830

600

7070

2.40

5370

10610

3.00

8510

14140

3.70

11610

- 8

4.0

14.3

590

750

1470

1.97

- 6

9.8

17.8

800

990

2000

1.28

- 2

15.3

22.0

900

1130

2240

1.18

- 9

3.2

13.6

520

660

1310

2.39

- 8

8.8

17.0

780

980

1950

1.39

- 4

14.0

21.0

910

1140

2270

1.27

- 9

2.4

13.1

450

570

1130

3.02

- 9

8.1

16.5

760

960

1900

1.52

- 6

13.0

20.2

890

1120

2230

1.37

-21

5.1

12.2

460

570

1140

1.44

-18

10.3

16.3

650

820

1630

1.21

-14

15.3

20.6

780

980

1950

1.19

-22

4.5

11.6

420

530

1060

1.59

-19

9.4

15.5

630

780

1560

1.30

-16

14.2

19.6

760

950

1890

1.27

-23

4.0

11.1

390

490

970

1.76

-21

8.7

14.9

590

740

1480

1.39

-18

13.3

18.9

730

910

1820

1.36

-40

3.6

8.6

280

360

700

1.37

-38

6.1

10.8

390

480

980

1.22

-35

10.8

15.2

540

680

1360

1.18

-32

15.5

19.5

670

840

1670

1.21

-39

5.6

10.2

360

450

890

1.29

-36

10.1

14.5

520

640

1290

1.25

-34

14.6

18.7

640

800

1590

1.29

-40

5.1

9.7

330

410

830

1.37

-37

9.5

13.9

490

610

1210

1.33

-35

14.0

18.1

610

760

1520

1.37

* fTI - Mean Point of Impact

4C—2-34-1—1—(207—5)

Figure 6-21B (Sheet 5 of 9)

Change 6

6 -68S

T.O. 1F-4C-34-1-1

ME TOSS RIPPLE RELEASE

CBU-52A/B

3.0 G PULLOUT
0.14 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

BIST/
MPI* C
LAS]

WCE BETWEEN
)F FIRST AND
CLUSTER

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

SOO

3420

3.92

2540

- 8

4.0

14.3

820

1050

2070

1.97

5130

4.34

4200

- 6

9.9

17.8

1120

1410

2800

1.28

6840

5.32

5860

- 2

15.3

22.0

1260

1580

3140

1.18

550

3420

3.92

2420

- 9

3.2

13.6

730

930

1840

2.39

5130

4.20

4090

- 8

8.8

17.0

1090

1380

2730

1.39

6840

5.04

5720

- 4

13.9

20.9

1260

1580

3180

1.27

600

3420

4.06

2280

- 9

2.4

13.2

630

800

1600

3.03

5130

4.20

3970

- 9

8.1

16.5

1060

1340

2650

1.52

6840

4.90

5590

- 6

12.9

20.0

1240

1550

3130

1.37

500

5000

3.08

3800

-21

5.1

12.1

630

800

1580

1.44

7500

3.78

6100

-18

10.2

16.2

910

1140

2280

1.21

10000

4.76

8360

-14

15.3

20.6

1100

1370

2730

1.19

550

5000

3.08

3670

-22

4.5

11.6

590

740

1470

1.59

7500

3.78

5940

-19

9.4

15.6

880

1100

2200

1.30

10000

4.48

8230

-16

14.1

19.5

1050

1320

2630

1.27

600

5000

3.08

3540

-23

3.9

11.1

540

680

1360

1.77

7500

3.64

5830

-20

8.7

14.9

830

1040

2070

1.39

10000

4.48

8040

-17

13.4

18.9

1020

1280

2550

1.36

500

5300

7.5

2.24

3970

-39

3.6

8.6

390

490

950

1.37

7070

2.52

5590

-38

6.0

10.8

530

670

1330

1.22

10610

3.08

8820

-36

10.8

15.1

760

950

1990

1.18

14140

3.78

12000

-33

15.4

19.5

930

1170

2350

1.21

550

7070

2.38

5520

-39

5.6

10.2

500

620

1220

1.29

10610

3.08

8640

-36

10.1

14.5

720

900

1800

1.25

14140

3.78

11780

-34

14.6

18.7

890

1120

2230

1.30

600

7070

2.38

5380

-40

5.1

9.7

460

580

1140

1.37

10610

3.08

8460

-37

9.5

13.9

680

850

1700

1.33

14140

3.64

11650

-35

13.9

18.1

850

1060

2120

1.37

* "PI - ffean Point of Impact

4C—34—1—1—(207—6)

Figure 6-21B (Sheet 6 of 9)

6-68T

Change 6

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

CBU-52A/B

4.0 G PULLOUT
0.06 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLI

COND

[TICNS

MIDDLE BOMB IN RIPPLE RELEASE

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

■

BSii

Brcinnn

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

“Time

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

ki?Sh

BOMB

STICK

(FT)

•

500

3420

5130

6840

3.06

3.48

4.20

2730

4410

6100

- 7

- 4
+ 1

5.0

11.0

16.8

14.9

18.8

23.3

520

660

710

650

830

890

1300

1650

1780

1.73

1.24

1.16

•

550

3420

5130

6840

3.06

3.36

4.02

2640

4320

5980

- 8
- 6
- 2

4.2

9.9

15.4

14.3

17.9

22.1

480

650

730

610

820

920

1210

1630

1830

2.00

1.34

1.25

600

3420

5130

6840

3.06

3.30

3.96

2560

4230

5870

- 9

- 8
- 4

3.5

9.1

14.4

13.8

17.3

21.3

430

630

730

550

790

910

1090

1570

1810

2.36

1.46

1.35

500

5000

7500

10000

2.58

3.12

3.78

4010

6360

8720

-20

-17

-12

5.7

11.1

16.4

12.7
17.1

21.7

390

540

630

480

680

790

960

1350

1570

1.38

1.19

1.17

550

5000

7500

10000

2.52

3.00

3.66

3920

6260

8590

-21

-18

-IS

5.1

10.2

15.3

12.1

16.2

20.7

360

520

620

450

650

780

900

1290

1550

1.50

1.27

1.26

600

5000

7500

10000

2.52

3.00

3.60

3810

6140

8450

-22

-19

-16

4.6

9.6
14.4

11.6

15.7

19.9

330

490

600

420

620

750

840

1230

1490

1.65

1.37

1.35

500

5300

7070

10610

14140

7.5

1.92

2.10

2.58

3.12

4170

5840

9130

12410

-39

-38

-35

-31

3.9

6.5

11.4

16.3

8.9

11.2

15.8

20.4

230

320

450

550

290

400

560

680

560

780

1120

1370

1.34

1.20

1.17

1.20

550

5300

7070

10610

14140

7.5

1.86

2.04

2.52

3.06

4090

5750

9010

12250

-40

-39

-36

-33

3.5

6.0

10.7

15.5

8.4

10.6

15.1

19.6

210

300

420

520

260

370

530

650

510

720

1060

1310

1.42

1.27
1.24

1.28

600

45 7070

10610
14140

2.04

2.52

3.00

5630

8860

12110

-39

-37

-34

5.5

10.1

14.8

10.1

14.5

18.9

270

400

500

340 670

500” 1000
620 1240

1.35

1.32

1.37

* >TI - Mean Point of Tinpact

Figure 6-21B (Sheet 7 of 9)

1—(207-7)

Change 6

6-68U

T.O. 1F-4C-34-1-1

VIVE TOSS RIPPLE RELEASE

CBU-52A/B

4.0 G PULLOUT
0.10 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE T

iELEASE

DTST7
MPI* C
LAS!

JCETiT
)F FIRS
CLUS1

TWEET
T AND
ER

WRCS

”

PICKLE

TIME

c D

CLUSTER

RELEASE

KNOTS

dive

ALT

SLANT

RELEASE

FUNCTION

BOMB

SETTING

TAS

ANGLE

AGL

RANGE

TIME

ALTITUDE

ANGLE

TIME

IMPACT

STICK

(DEG)

(FT)

(1000 FT)

(SEC)

(FT)

(DEG)

(SEC)

(FT)

SOO

3420

3.10

2730

- 7

5.1

15.0

870

1110

2190

1.73

5130

3.50

4410

- 4

11.1

18.9

1110

1390

2770

1.24

6840

4.20

6100

+ 1

16.8

23.3

1180

1480

2950

1.16

550

3420

3.10

2640

- 8

4.2

14.4

810

1030

2040

2.00

5130

3.40

4310

- 6

10.0

18.0

1090

1380

2730

1.34

6840

4.00

5980

- 3

15.3

22.1

1220

1530

3060

1.25

600

3420

3.10

2550

- 9

3.5

13.9

730

930

1830

2.37

5130

3.30

4230

- 8

9.1

17.3

1040

1320

2600

1.46

6840

3.90

5880

- 5

14.2

21.2

1200

1510

3030

1.35

500

5000

2.60

4000

-20

5.8

12.8

650

810

1620

1.38

7500

3.10

6370

-17

11.2

17.1

900

1130

2250

1.19

10000

3.80

8720

-12

16.5

21.8

1050

1320

2630

1.17

550

5000

2.50

3930

-21

5.1

12.1

600

750

1500

1.50

7500

3.00

6270

-18

10.2

16.3

860

1080

2150

1.27

10000

3.60

8610

-15

15.2

20.6

1030

1290

2590

1.26

600

5000

2.50

3820

-22

4.6

11.6

560

700 1400

1.65

7500

3.00

6140

-19

9.6

15.7

830

1040 2060

1.37

10000

3.60

8460

-16

14.5

19.9

1000

1250 2490

1.35

500

5300

7.5

1.90

4180

-39

3.9

8.9

380

480 910

1.33

7070

2.10

5840

-38

6.5

11.2

530

660 1280

1.20

10610

2.60

9120

-35

11.4

15.8

750

940 1870

1.17

14140

3.10

12420

-31

16.3

20.4

910

1140 2270

1.20

550

5300

7.5

1.90

4070

-40

3.5

8.4

350

440 840

1.42

7070

2.10

5720

-38

5.9

10.6

490

620 1190

1.28

10610

2.50

9020

-36

10.7

15.0

700

880 1760

1.24

14140

3.00

12280

-33

15.4

19.5

870

1090 2170

1.28

600

7070

2.00

5660

-40

5.5

10.1

450

560 1090

1.35

10610

2.50

8870

-37

10.1

14.5

670

830 1660

1.32

14140

3.00

12110

-34

14.8

18.9

830

1030 2070

1.37

* »«PI - »fean Point of Impact

4C—34—1—1—(207—8)

Figure 6-21B (Sheet 8 of 9)

6-68V

Change 6

T.O. 1F-4C-34-1-1

DIVE JOSS RIPPLE RELEASE Hg

CBU-52A/B

4.0 G PULLOUT
0.14 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BCMB IN RIPPLE RELEASE

dist;

MPI* C
IASI

VJCE BI
)F FIR?
CLUS1

5TWEEN
5T AND
rER

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

FICKLE^

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BCMB

STICK

(FT)

BCMB

STICK

(FT)

BCMB

STICK

(FT)

500

3420

3.08

2730

- 7

5.0

14.9

1200

1540

3040

1.74

5130

3.50

4400

- 4

11.0

18.8

1540

1940

3840

1.24

6840

4.20

6090

16.7

23.2

1660

2070

4120

1.16

550

3420

3.08

2640

- 8

4.2

14.3

1120

1440

2830

2.02

5130

3.36

4310

- 7

9.8

17.8

1510

1910

3770

1.34

6840

4.06

5970

- 2

15.3

22.1

1710

2150

4260

1.25

600

3420

3.08

2550

- 9

3.5

13.8

1000

1280

2550

2.38

5130

3.36

4210

- 8

9.1

17.3

1470

1860

3670

1.46

6840

3.92

5860

- 5

14.2

21.1

1670

2110

4180

1.35

500

5000

2.52

4030

-20

5.7

12.7

890

1120

2230

1.38

7500

3.08

6370

-17

11.1

17.0

1250

1580

3130

1.19

10000

3.78

8720

-12

16.4

21.7

1470

1850

3670

1.17

550

5000

2.52

3920

-21

5.1

12.1

840

1060

2090

1.50

7500

3.08

6240

-18

10.3

16.4

1210

1530

3040

1.28

10000

3.64

8590

-IS

15.3

20.6

1440

1810

3600

1.26

600

5000

2.52

3810

-22

4.6

11.6

780

980

1940

1.65

7500

2.94

6160

-20

9.5

15.6

1140

1440

2860

1.37

10000

3.64

8440

-16

14.5

20.0

1400

1760

3490

1.35

500

5300

7.5

1.96

4150

-39

3.9

8.9

530

670

1260

1.34

7070

2.10

5840

-38

6.5

11.2

720

910

1740

1.20

10610

2.66

9090

-34

11.5

15.8

1050

1320

2620

1.17

14140

3.08

12420

-31

16.3

20.3

1270

1590

3200

1.20

550

5300

7.5

1.82

4120

-40

3.5

8.4

460

590

1120

1.42

7070

2.10

5720

-39

5.9

10.6

680

850

1630

1.28

10610

2.52

9010

-36

10.7

15.0

980

1240

2440

1.24

14140

3.08

12240

-33

15.5

19.6

1220

1530

3040

1.28

600

7070

2.10

5590

-39

5.5

10.1

630

790

1520

1.36

10610

2.52

8860

-37

10.1

14.5

930

1170

2310

1.32

14140

3.08

12060

-34

14.8

18.9

1160

1450

2900

1.37

♦ MPI - Mean Point of Impact

4C-34-1

Figure 6-21B (Sheet 9 of 9)

Change 6

1—(207—9;

6-68W

T.O. 1F-4C-34-1-1

dm TOSS RIPPLE RELEASE

CBU-52B/B DISPENSER AND BOMB

2.0 G PULLOUT
.06 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI* OF FIRST AND

LAST CLUSTER

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

WRCS

SETTING

500

5130

6.56

3680

- 8

7.9

16.4

280

350

720

1.52

6840

8.12

5230

- 5

13.2

20.2

330

410

830

1.39

550

5130

6.26

3530

-10

6.8

15.5

280

340

690

1.67

6840

7.64

5050

- 7

11.7

19.1

330

410

830

1.48

600

5130

6.14

3380

-11

5.9

14.8

260

330

660

1.85

6840

7.40

4870

- 8

10.7

18.2

330

410

810

1.57

500

5000

4.54

3210

-22

3.7

11.1

160

190

390

1.77

7500

4.60

5690

-22

8.9

14.9

250

290

580

1.37

10000

7.06

7460

-17

13.4

19.1

290

360

720

1.38

550

5000

4.42

3070

-23

3.1

10.5

130

170

350

1.99

7500

5.38

5210

-21

7.9

14.3

230

290

570

1.47

10000

6.76

7250

-18

12.3

18.1

280

350

700

1.45

600

7500

5.26

5040

-22

7.1

13.6

220

270

540

1.57

10000

6.58

7050

-19

11.5

17.3

270

340

680

1.52

500

10610

4.44

8000

-36

9.9

14.4

200

260

510

1.32

14140

5.58

10930

-34

14.3

18.6

250

310

630

1.38

550

10610

4.32

7810

-37

9.1

13.7

190

240

480

1.38

14140

5.40

10701

-35

13.4

17.7

240

300

600

1.45

600

10610

4.20

7650

-38

8.5

13.1

180

230

460

1.45

14140

5.28

10490

-36

12.7

17.0

230

290

570

1.51

* MEAN POINT OF IMPACT

4C-34

- 1 - 1 -( 220 - 1 )

Figure 6-21C (Sheet 1 of 9)

6-68X Change 7

T.O. 1F-4C-34-1-1

VIVE TOSS RIPPLE RELEASE

CBU-52B/B DISPENSER AND BOMB

2.0 G PULLOUT
.10 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE

CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANC
MPI* OF
LAST

E BETWE
FIRST A
CLUSTEF

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

WRCS

SETTING

500

5130

6.50

3680

- 8

7.9

16.3

470

590

1190

1.52

6840

8.10

5230

- 5

13.2

20.2

550

690

1370

1.39

550

5130

6.30

3530

-10

6.8

15.5

460

580

1150

1.67

6840

7.70

5040

- 7

19.1

11.8

550

690

1380

1.48

600

5130

6.10

3390

-11

5.9

14.8

440

550

1090

1.85

6840

7.40

4870

- 8

18.2

10.7

540

680

1360

1.57

500

5000

4.50

3230

-22

3.7

11.1

260

320

650

1.76

7500

5.60

5370

-20

8.7

15.1

400

500

990

1.39

10000

6.20

7690

-18

13.3

18.8

470

590

1170

1.37

550

7500

6.40

5210

-21

7.9

14.3

380

480

950

1.48

10000

6.70

7270

-18

12.3

18.0

470

580

1170

1.45

600

7500

5.20

5070

-22

7.2

13.6

360

450

890

1.56

10000

6.60

7040

-19

11.5

17.3

450

560

1130

1.52

500

10610

4.50

7970

-36

9.9

14.4

340

430

850

1.32

14140

5.50

10970

-34

14.3

18.6

420

520

1050

1.38

550

10610

4.30

7820

-37

9.1

13.7

320

400

720

1.38

14140

5.40

10700

-35

13.4

17.7

400

500

1000

1.45

600

10610

4.20

7650

-38

8.5

13.1

300

380

760

1.45

14140

5.30

10470

-36

12.7

17.0

380

480

960

1.51

* MEAN POINT OF IMPACT

Figure 6-21C (Sheet 2 of 9)

4C—34-1-1 -(220 -2)

Change 7

6-68Y

T.O. 1F-4C-34-1-1

(CONTINUED)

■■' ’ •' ’• '''

CBU-52B/B DISPENSER AND BOMB

2.0 G PULLOUT
.14 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

DISTANCE BETWEEN
MPI* OF FIRST AND

PICKLE CONDITIONS MIDDLE BOMB IN RIPPLE RELEASE _LAST CLUSTER

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

WRCS

SETTING

500

5130

6.58

3670

- 8

7.9

16.3

670

840

1670

1.52

6840

8.12

5230

- 5

13.2

20.2

770

970

1920

1.39

550

5130

6.16

3550

-10

6.8

15.4

640

810

1610

1.67

6840

7.70

5040

- 7

11.8

19.1

770

960

1920

1.48

600

5130

6.16

3370

-11

5.9

14.8

610

770

1530

1.85

6840

7.42

4860

- 8

10.7

18.2

760

950

1900

1.57

500

5000

4.56

3200

-22

3.7

11.1

360

450

900

1.78

7500

5.68

5350

-20

8.7

15.1

550

690

1390

1.39

10000

7.08

7450

-17

13.4

19.1

670

840

1680

1.38

550

7500

5.40

5200

-21

7.9

14.3

530

670

1320

1.48

10000

6.80

7240

-18

12.3

18.1

650

820

1640

1.45

600

7500

5.26

5040

-22

7.1

13.6

500

620

1250

1.57

10000

6.52

7070

-20

11.5

17.3

630

790

1570

1.52

500

10610

4.48

7980

-36

9.9

14.4

480

600

1190

1.32

14140

5.60

10910

-34

14.3

18.6

590

730

1460

1.38

550

7500

5.40

5200

-21

7.9

14.3

530

670

1320

1.48

10000

6.80

7240

-18

12.3

18.1

650

820

1640

1.45

600

7500

5.26

5040

-22

7.1

13.6

500

620

1250

1.57

10000

6.52

7070

-20

11.5

17.3

630

790

1570

1.52

500

10610

4.48

7980

-36

9.9

14.4

480

600

1190

1.32

14140

5.60

10910

-34

14.3

18.6

590

730

1460

1.38

550

10610

4.34

7800

-37

9.1

13.6

450

560

1120

1.38

14140

5.46

10660

-35

13.4

17.7

560

700

1400

1.45

600

10610

4.20

7650

-38

8.5

13.1

430

530

1060

1.45

14140

5.32

10460

-36

12.7

17.0

530

670

1340

1.51

* MEAN POINT OF IMPACT

4C-34-1 -1 -{220-3)

Figure 6-21C (Sheet 3 of 9)

6-68Z

Change 7

T.O. 1F-4C-34-1-1

D/I/E TOSS RIPPLE RELEASE

F-4E

CBU-52B/B DISPENSER AND BOMB

3.0 G PULLOUT
.06 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN
MPI* OF FIRST AND
LAST CLUSTER

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

■Sflli

BOMB

STICK

(FT)

BOMB

STICK

(FT)

WRCS

SETTING

500

3420

3.98

2530

- 7

4.1

14.4

350

440

880

2.07

5130

4.64

4180

- 5

10.6

18.6

460

570

1140

1.42

6840

5.84

5860

16.9

23.4

480

600

1190

1.38

550

3420

3.98

2410

- 9

3.2

13.8

310

390

780

2.49

5130

4.46

4060

- 7

9.4

17.6

540

570

1140

1.52

6840

5.48

5700

- 3

15.1

22.0

500

630

1240

1.44

600

5130

4.34

3950

- 8

8.4

16.8

440

560

1110

1.64

6840

5.72

5520

- 3

14.5

21.6

520

650

1290

1.54

500

5000

3.22

3760

-21

5.2

12.5

270

340

680

1.55

7500

4.06

6020

-17

10.8

17.0

380

470

950

1.36

10000

5.08

8290

-13

16.3

21.7

440

550

1100

1.37

550

5000

3.16

3640

-22

4.6

11.8

250

320

630

1.69

7500

3.88

5900

-19

9.8

16.0

370

460

910

1.43

10000

4.84

8130

-15

15.0

20.5

440

550

1090

1.44

600

5000

3.10

3530

-22

4.0

11.2

230

290

580

1.85

7500

3.82

5760

-20

9.1

15.3

350

440

890

1.51

10000

4.72

7970

-17

14.0

19.6

430

530

1060

1-52

500

5300

7.5

2.28

3950

-39

3.6

8.8

170

210

440

1.45

7070

2.58

5560

-38

6.3

11.1

230

290

570

1.32

10610

3.30

8710

-35

11.3

15.8

320

400

800

1.31

14140

4.02

11900

-31

16.3

20.5

390

490

980

1.37

550

5300

7.5

2.22

3850

-40

3.2

8.2

160

200

390

1.54

7070

2.52

5440

-39

5.7

10.5

270

320

590

1.38

10610

3.18

8580

-36

10.5

15.0

310

380

760

1.37

14140

3.90

11720

-33

15.3

19.6

370

470

930

1.44

600

7070

2.46

5330

-39

5.2

9.9

200

250

500

1.46

10610

3.12

8440

-37

9.9

14.4

290

360

730

1.44

14140

3.84

11530

-34

14.6

18.8

360

450

900

1.52

* MEAN POINT OF IMPACT

4C-34-1 -1 -(220-4)

Figure 6-21C (Sheet 4 of 9)

Change 7

6-68AA

T.O. 1F-4C-34-1-1

VIVE TOSS RIPPLE RELEASE

CBU-52B/B DISPENSER AND BOMB

3.0 G PULLOUT
.10 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI*OF FIRST AND

LAST CLUSTER

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

WRCS

SETTING

500

3420

4.00

2530

- 7

4.2

14.4

740

900

1630

2.07

5130

4.60

4180

- 5

10.6

18.5

760

950

1890

1.42

6840

7.0

5.80

5860

16.8

23.4

800

990

1990

1.38

550

3420

4.00

2410

- 8

3.2

13.8

520

660

1320

2.49

5130

4.40

4070

- 7

9.3

17.5

750

950

1880

1.52

6840

5.50

5700

- 3

15.1

22.0

840

1050

2080

1.45

600

5130

4.30

3960

- 8

8.4

16.8

730

920

1840

1.64

6840

5.30

5550

- 5

13.9

20.9

840

1050

2100

1.53

500

5000

3.20

3760

-21

5.2

12.4

450

570

1130

1.55

7500

4.10

6010

-17

10.8

17.0

630

800

1590

1.36

10000

5.10

8290

-13

16.3

21.8

730

920

1830

1.37

550

5000

3.20

3630

-21

4.6

11.8

420

530

1050

1.69

7500

3.90

5900

-19

9.8

16.1

610

760

1530

1.43

10000

4.90

8120

-15

15.0

20.6

730

910

1820

1.44

600

5000

3.10

3530

-22

4.0

11.2

380

480

970

1.85

7500

3.80

5770

-20

9.1

15.3

590

730

1470

1.51

10000

4.70

7980

-17

14.0

19.6

710

880

1760

1.51

500

5300

7.5

2.30

3940

-39

3.6

8.7

280

350

700

1.45

7070

2.60

5540

-38

6.2

11.1

380

480

960

1.32

10610

3.30

8710

-35

11.3

15.8

530

670

1540

1.31

14140

4.00

11900

-31

16.3

20.5

650

810

1630

1.37

550

5300

7.5

2.20

3860

-40

3.2

8.2

260

320

640

1.53

7070

2.50

5450

-39

5.7

10.5

360

450

890

1.38

10610

3.20

8570

-36

10.5

15.0

510

640

1280

1.37

14140

3.90

11720

-33

15.3

19.6

620

780

1560

1.44

600

7070

2.40

5370

-40

5.2

10.0

330

420

830

1.45

10610

3.10

8450

-37

9.9

14.4

480

610

1210

1.44

14140

3.90

11500

-34

14.6

18.8

600

750

1490

1.52

* MEAN POINT OF IMPACT

4C-34-1

-1.(220-5)

Figure 6-21C (Sheet 5 of 9)

6-68AB

Change 7

T.O. 1F-4C-34-1-1

D/I/E JOSS RIPPLE RELEASE

F-4E

(CONTINUED)

CBU-52B/B DISPENSER AND BOMB

3.0 G PULLOUT
.14 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI*OF FIRST AND

LAST CLUSTER

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

WRCS

SETTING

500

3420

4.06

2520

- 7

4.2

14.5

830

1050

2140

2.07

5130

4.62

4180

- 5

10.6

18.5

1160

1330

2650

1.42

6840

5.88

5850

16.9

23.5

1110

1390

2780

1.38

550

3420

4.06

2400

- 8

3.2

13.8

740

940

1930

2-49

5130

4.48

4060

- 7

9.4

17.6

1060

1330

2650

1.52

6840

5.46

5700

- 3

15.1

21.9

1160

1460

2910

1.45

600

5130

4.34

3950

- 8

8.4

16.8

1030

1300

2600

1.64

6840

5.32

5550

- 5

13.9

21.0

1170

1470

2930

1.54

500

5000

3.20

3760

-21

5.2

12.4

630

790

1580

1.55

7500

4.04

6030

-17

10.8

17.0

880

1110

2210

1.36

10000

5.12

8280

-12

16.3

21.8

1030

1290

2560

1.37

550

5000

3.20

3630

-21

4.6

11.8

590

740

1470

1.69

7500

3.90

5900

-19

9.8

16.0

850

1080

2140

1.43

10000

4.84

8130

-15

15.0

20.5

1010

1270

2530

1.44

600

5000

3.06

3550

-23

4.0

11.2

540

680

1360

1.84

7500

3.76

5780

-20

9.0

51.3

820

1030

2050

1.51

10000

4.70

7970

-17

14.0

19.6

980

1240

2450

1.51

500

5300

7.5

2.32

3930

-39

3.6

8.7

400

500

990

1.46

7070

2.66

5510

-38

6.2

11.1

530

670

1330

1.32

10610

3.36

8680

-34

11.3

15.8

750

940

1880

1.31

14140

4.06

11870

-31

16.3

20.5

910

1140

2270

1.37

550

7070

2.52

5440

-39

5.7

10.5

500

620

1240

1.38

10610

3.22

8560

-36

10.5

15.0

710

890

1780

1.37

14140

3.92

11700

-33

15.3

19.5

870

1090

2180

1.44

600

7070

2.52

5290

-39

5.1

9.9

460

580

1150

1.46

10610

3.08

8460

-37

9.9

14.4

670

840

1680

1.44

14140

3.78

11560

-34

14.6

18.8

830

1040

2080

1.51

* MEAN POINT OF IMPACT

Figure 6-21C (Sheet 6 of 9)

4C-34-1 -1 -(220-6)

Change 7

6-68AC

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

CBU-52B/B DISPENSER AND BOMB

4.0 G PULLOUT
.06 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI*OF FIRST AND

LAST CLUSTER

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

WRCS

SETTING

500

3420

3.18

2720

- 6

5.3

15-3

510

640

1270

1.83

5130

3.74

4390

- 3

11.9

19.7

600

760

1510

1.40

550

3420

3.12

2630

- 8

4.3

14.5

570

600

1180

2.10

5130

3.56

4290

- 5

10.5

18.5

610

770

1580

1.48

6840

4.40

5960

- 0

16.8

23.4

650

810

1620

1.44

600

3420

3.12

2540

- 9

3.6

13.9

430

540

1070

2.45

5130

3.50

4200

- 7

9.6

17.8

610

770

1580

1.59

6840

4.28

5840

- 3

15.5

22.3

660

830

1650

1.52

500

5000

2.68

3980

-19

6-0

13.1

360

470

930

1.50

7500

3.34

6310

-15

11.9

18.0

510

640

1280

1.34

10000

4.12

8660

-10

17.8

23.1

570

720

1430

1.36

550

5000

2.62

3880

-21

5.3

12.4

360

450

900

1.61

7500

3.16

6210

-18

10.8

16.9

500

620

1240

1.41

10000

3.94

8520

-13

16.4

21.8

580

730

1450

1.43

600

5000

2.56

3800

-22

4.7

11.8

330

420

840

1.74

7500

3.10

6100

-19

10.0

16.2

480

600

1200

1.50

10000

3.82

8390

-15

15.3

20.8

570

710

1420

1.51

500

5300

7.5

1.98

4140

-39

4.0

9.2

230

280

570

1.43

7070

2.22

5780

-37

6.7

11.6

310

390

780

1.31

10610

2.70

9070

-34

12.0

16.5

440

550

1090

1.31

14140

3.30

12330

-28

17.3

21.5

520

660

1310

1.36

550

5300

7.5

1.92

4050

-40

3.6

8.5

210

270

520

1.50

7070

2.10

5720

-38

6.1

10.9

290

370

730

1.36

10610

2.64

8940

-35

11.2

15.7

410

520

1040

1.37

14140

3.18

12190

-32

16.3

20.5

500

630

1260

1.43

600

5300

7.5

1.86

3980

-40

3.2

8.1

190

240

470

1.59

7070

2.10

5590

-39

5.6

10.4

270

340

680

1.44

10610

2.58

8820

-36

10.6

15.0

390

480

980

1.44

14140

3.18

12000

-33

15.5

19.8

480

610

1210

1.51

* MEAN POINT OF IMPACT

4C-34-1-1-1220-7)

Figure 6-21C (Sheet 7 of 9)

6-68AD

Change 7

T.O. 1F-4C-34-1-1

VIVE TOSS RIPPLE RELEASE ggj

CBU-52B/B DISPENSER AND BOMB

4.0 G PULLOUT
.10 SEC RELEASE INTERVAL
HOB -1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN
MPI*OF FIRST AND
LAST CLUSTER

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

WRCS

SETTING

500

3420

3.20

2720

- 6

5.3

15.3

850

1080

2140

1.83

5130

3.70

4400

- 3

11.9

19.2

1000

1260

2500

1.39

550

3420

3.10

2640

- 8

4.3

14.4

780

990

1960

2.11

5130

3.60

4290

- 5

10.7

18.7

1030

1290

2560

1.48

6840

4.40

5960

- 0

16.8

23.4

1080

1350

2690

1.44

600

3420

3.10

2550

- 9

3.6

13.9

710

900

1790

2.46

5130

3.50

4200

- 7

9.7

17.8

1010

1270

2520

1.59

6840

4.30

5840

- 2

15.6

22.4

1110

1390

2760

1.53

500

5000

2.70

3970

-19

6.0

13.2

640

800

1600

1.50

7500

3.40

6290

-15

11.8

17.9

850

1070

2130

1.34

10000

4.10

8660

-10

17.8

23.1

950

1190

2380

1.36

550

5000

2.60

3890

-21

5.3

12.4

600

760

1520

1.61

7500

3.20

6200

-17

10.8

17.0

830

1050

2080

1.41

10000

3.90

8530

-13

16.3

21.7

1000

1210

2410

1.43

600

5000

2.60

3780

-22

4.7

11.8

560

710

1410

1.75

7500

3.10

6100

-19

10.0

16.2

800

1000

2000

1.50

10000

3.80

8390

-15

15.3

20.8

940

1190

2360

1.51

500

5300

7.5

2.00

4130

-39

4.0

9.1

380

480

940

1.43

7070

2.20

5790

-37

6.7

11.6

530

660

1290

1.31

10610

2.70

9070

-34

12.0

16.5

730

910

1820

1.31

14140

3.30

12330

-30

17.3

21.5

870

1090

1280

1.36

550

5300

7.5

1.90

4070

-40

3.6

8.5

340

440

840

1.49

7070

2.10

5720

-38

6.1

10.9

490

610

1180

1.36

10610

2.60

8960

-35

11.2

15.7

690

870

1730

1.37

14140

3.20

12180

-32

16.3

20.5

840

1050

2100

1.43

600

5300

7.5

1.90

3950

-40

3.2

8.1

310

1.60

7070

1.90

5720

^»0

5.7

10.4

450

560

1080

1.43

10610

2.60

8810

-36

10.5

15.0

750

820

1640

1.44

14140

3.20

11990

-33

15.5

19.8

810

1010

2020

1.52

* MEAN POINT OF IMPACT

Figure 6-21C (Sheet 8 of 9)

4C-34-1—1 -{220-8)

Change 7

6-68AE

CBU-52B/B DISPENSER AND BOMB

4.0 G PULLOUT
.14 SEC RELEASE INTERVAL
HOB- 1800 FT AGL

DISTANCE BETWEEN
MPI*OF FIRST AND

PICKLE CONDITIONS MIDDLE BOMB IN RIPPLE RELEASE LAST CLUSTER

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

WRCS

SETTING

500

3420

3.18

2710

- 6

5.2

15.2

1180

1510

2970

1.83

5130

3.75

4390

- 3

12.0

19.7

1410

1770

3530

1.40

550

3420

3.18

2620

- 8

4.4

14.6

1110

1420

2820

2.11

5130

3.60

4290

- 5

10.6

186

1430

1800

3610

1.48

6840

4.48

5960

17.0

23.6

1510

1890

3780

1.44

600

3420

3.18

2530

- 9

3.6

14.0

1010

1290

2580

2.47

5130

3.46

4200

- 7

9.5

17.7

1390

1760

3520

1.59

6840

4.20

5840

- 3

15.3

22.1

1530

1920

3850

1.52

500

5000

2.64

3990

-20

5.9

13.1

900

1140

2270

1.50

7500

3.34

6300

-15

11.9

18.0

1200

1510

2990

1.35

10000

4.18

8650

-10

17.9

23.3

1340

1680

3340

1.36

550

5000

2.64

3880

-21

5.3

12.4

850

1070

2140

1.61

7500

3.20

6200

-17

10.8

17.0

1160

1470

2910

1.41

10000

3.90

8530

-13

16.3

21.7

1420

1760

3520

1.43

600

5000

2.50

3820

-22

4.7

11.7

790

1000

1990

1.74

7500

3.06

6110

-19

9.9

16.1

1110

1400

2830

1.50

10000

3.76

8400

-15

15.2

20.7

1310

1650

3320

1.51

500

5300

7.5

1.90

4180

-39

4.0

9.1

510

650

1240

1.41

7070

2.24

5760

-37

6.7

11.6

730

920

1770

1.31

10610

2.80

9020

-33

12.1

16.6

1020

1280

2550

1.31

14140

3.35

12290

-30

17.3

21.5

1220

1530

3050

1.36

550

5300

7.5

1.90

4070

^*0

3.6

8.5

470

600

1140

1.49

7070

2.10

5710

-39

6.1

10.9

670

840

1600

1.36

10610

2.66

8920

-35

11.2

15.7

970

1220

2420

1.37

14140

3.22

12160

-32

16.3

20.5

1170

1470

2940

1.44

600

7070

2.10

5590

-39

5.6

10.4

630

790

1510

1.44

10610

2.66

8770

-36

10.5

15.0

920

1050

2210

1.44

14140

3.22

11970

-33

15.5

19.7

1130

1410

2800

1.52

* MEAN POINT OF IMPACT

4C-34-1 -I -(220-9)

Figure 6-21C (Sheet 9 of 9)

6-68AF

Change 7

T.O. 1F-4C-34-1-1

VIVE TOSS RIPPLE RELEASE

CBU-58/B or CBU-71/B DISPENSER and BOMB

2.0 G PULLOUT
.06 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE

CONDITIONS

MIDDLE BCMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI* OF FIRST AND

LAST CLUSTER

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

500

5130

6.62

3670

-8

7.9

16.9

280

350

720

1.57

6840

8.12

5230

-5

13.1

20.7

330

410

830

1.40

550

5130

6.38

3510

-9

6.8

16.1

280

350

690

1.74

6840

7.70

5040

-7

11.8

19.6

330

420

830

1.49

600

5130

6.26

3350

-10

5.9

15.4

260

330

650

1.95

6840

7.40

4870

-8

10.7

18.7

330

410

820

1.59

500

5000

4.68

3170

-22

3.6

11.7

150

190

370

1.93

7500

5.70

5340

-20

8.7

15.6

240

300

590

1.42

10000

7.08

7450

-17

13.4

19.5

290

360

720

1.38

550

7500

5.46

5180

-21

7.8

14.8

220

280

560

1.51

10000

6.78

7240

-18

12.3

18.5

280

350

700

1.46

600

7500

5.28

5030

-22

7.1

14.1

210

270

530

1.61

10000

6.60

7040

-19

11.4

17.7

270

340

670

1.53

500

45 10610

4.44

8000

-36

9.9

14.8

200

260

510

1.33

14140

5.52

10960

-34

14.3

18.9

250

310

630

1.38

550

45 :

10610

4.32

7810

-37

9.1

14.0

190

240

480

1.40

14140

5.34

10740

-35

13.4

18.1

240

300

600

1.44

600

45 10610

4.20

7650

-38

8.5

13.4

180

230

450

1.46

14140

5.28

10490

-36

12.7

17.4

230

290

570

1.51

* MEAN POINT OF IMPACT

4C—34— 1 — 1 —(219—1>

Figure 6-21D (Sheet 1 of 9)

Change 7 6-68AG

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

F-4E

(CONTINUED)

•vA '

CBU-58/B or CBU-71/B DISPENSER and BOMB

2.0 G PULLOUT
.10 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN
MPI* OF FIRST AND
LAST CLUSTER

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BCMB

STICK

(FT)

BOMB

STICK

(FT)

500

5130

6.60

3670

-8

7.9

16.9

470

600

1190

1.57

6840

8.10

5230

-5

13.1

20.7

560

700

1380

1.40

550

5130

6.40

3510

-9

6.8

16.1

460

580

1150

1.74

6840

7.70

5040

-7

11.8

19.6

550

690

1380

1.49

600

5130

6.20

3370

-11

5.9

15.4

440

570

1080

1.94

6840

7.40

4870

-8

10.7

18.7

540

680

1360

1.59

500

5000

4.70

3160

-22

3.6

11.7

250

310

620

1.94

7500

5.70

5340

-20

8.7

15.6

390

490

980

1.42

10000

7.10

7450

-17

13.4

19.5

480

600

1200

1.38

550

7500

5.50

5170

-21

7.8

14.8

380

470

940

1.51

10000

6.80

7240

-18

12.3

18.5

470

580

1170

1.46

600

7500

5.30

5030

-22

7.1

14.1

350

440

880

1.61

10000

6.60

7040

-19

11.4

17.7

450

560

1120

1. S3

500

10610

4.40

8020

-36

9.9

14.8

340

530

850

1.33

14140

5.50

10970

-34

14.3

18.9

420

520

1050

1.37

550

10610

4.30

7820

-37

9.1

14.0

320

400

800

1.39

14140

5.40

10700

-37

13.4

18.0

400

500

1000

1.44

600

10610

4.20

7650

-38

8.5

13.4

300

380

750

1.46

14140

5.30

10470

-36

12.7

17.4

380

480

950

1.51

* MEAN POINT OF IMPACT

4C-34-1-M2I9-2)

Figure 6-21D (Sheet 2 of 9)

6-68AH Change 7

T.O. 1F-4C-34-1-1

VIVE TOSS RIPPLE RELEASE

F-4E

CBU-58/B or CBU-71/B DISPENSER and BOMB

PICKLE CONDITIONS

2.0 G PULLOUT
.14 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

MIDDLE BCMB IN RIPPLE RELEASE

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

500

5130

6.58

6840

8.12

550

5130

6.44

6840

7.40

600

5130

6.30

6840

7.42

500

5000

4.68

7500

5.66

10000

7.06

550

7500

5.38

10000

6.78

600

7500

5.24

10000

6.64

500

10610

4.48

14140

5.60

550

10610

4.34

14140

5.32

600

10610

4.20

14140

5.32

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

3670

-8

7.9

5230

-5

13.1

3500

-9

6.8

5040

-7

11.7

3340

-10

5.9

4860

-8

10.7

3170

-22

3.6

5350

-20

8.7

7460

-17

13.4

5210

-21

7.8

7240

-18

12.3

5050

-22

7.1

7030

-19

11.4

79 80

-36

9.8

10910

-34

14.2

7800

-37

9.1

10740

-35

13.4

7650

-38

8.5

10460

-36

12.7

DISTANCE BETWEEN
MPI* OF FIRST AND
LAST CLUSTER

WRCS

SETTING

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BCMB

STICK

(FT)

BOMB

STICK

(FT)

16.9

660

840

1670

1.57

20.7

770

970

1920

1.40

16.1

640

810

1610

1.74

19.6

770

970

1940

1.49

15.4

610

770

1530

1.95

18.8

760

950

1900

1.60

11.7

350

430

870

1.93

15.6

550

690

1380

1.42

19.5

670

840

1680

1.38

14.8

530

660

1310

1.51

18.5

650

820

1630

1.46

14.1

490

610

1240

1.61

17.7

630

790

1570

1.53

14.7

480

590

1180

1.33

18.9

590

730

1460

1.38

14.0

450

560

1120

1.40

18.0

560

700

1390

1.44

13.4

420

530

1060

1.46

17.3

530

670

1340

1.51

* MEAN POINT OF IMPACT

4C-34-l-1-(219-3)

Figure 6-21D (Sheet 3 of 9)

Change 7

6-68AJ

T.O. 1F-4C-34-1-1

■

DIVE TOSS RIPPLE RELEASE

(CONTINUED)

CBU-58/B or CBU-71/B DISPENSER and BOMB

3.0 G PULLOUT
.06 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE

CONDITIONS

MIDDLE BCMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI* OF FIRST AND

LAST CLUSTER

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELFASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BCMB

STICK

(FT)

BOMB

STICK

(FT)

500

3420

4.10

2520

* 7

4.2

15.1

360

450

890

2.20

5130

4.64

4180

- 5

10.6

19.1

460

570

1140

1.44

6840

5.84

5860

16.9

23.9

480

600

1200

1.38

550

5130

4.46

4060

- 7

9.4

18.1

460

570

1140

1.55

6840

5.48

5700

- 3

15.1

22.5

500

630

1260

1.45

600

5130

4.34

3950

- 8

8.4

17.4

440

550

1100

1.69

6840

5.30

5550

- 5

13.8

21.4

510

640

1270

1.54

500

5000

3.34

3720

-20

5.2

13.1

270

340

670

1.64

7500

4.06

6020

-17

10.8

17.4

380

470

940

1.37

10000

5.08

8290

-13

16.3

22.1

440

550

1100

1.37

550

5000

3.22

3620

-21

4.5

12.3

250

310

620

1.80

7500

3.94

5890

-19

9.8

16.6

370

460

910

1.45

10000

4.84

8130

-15

15.0

21.0

440

550

1090

1.44

600

5000

3.22

3490

-22

4.0

11.8

230

280

570

2.01

7500

3.82

5760

-20

9.0

15.8

350

440

880

1.54

10000

4.72

7970

-17

14.0

20.1

430

530

1060

1.52

500

5300

7.5

2.34

3920

-39

3.6

9.2

170

210

420

1.54

7070

2.58

5560

-38

6.2

11.5

230

280

570

1.35

10610

3.30

8710

-35

11.3

16.2

320

400

810

1.32

14140

4.02

11900

-31

16.2

20.8

390

490

980

1.36

550

7070

2.52

5440

-39

5.7

10.9

210

270

530

1.42

10610

3.18

8580

-36

10.5

15.4

310

380

760

1.38

14140

3.90

11720

-33

15.3

19.9

370

470

940

1.44

600

7070

2.46

5330

-39

5.2

10.3

200

250

490

1.50

10610

3.12

8440

-37

9.9

14.7

290

360

720

1.45

14140

3.84

11530

-34

14.5

19.1

360

450

900

1.51

* MEAN POINT OF IMPACT

4C—34—1-1—(219—4)

6-68AK

Change 7

Figure 6-21D (Sheet 4 of 9)

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

CBU-58/B or CBU-71/B DISPENSER and BOMB

3.0 G I’ULLOUT
.10 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE

CONDITIONS

MIDDLE BCMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI* OF FIRST AND

LAST CLUSTER

WRCS

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

500

3420

4.10

2520

- 7

4.2

15.1

590

750

1490

2.20

5130

4.70

4180

- 4

10.7

19.2

760

960

1930

1.44

6840

5.80

5860

16.8

23.8

800

1000

2000

1.38

550

5130

4.50

4060

- 7

9.4

18.2

760

960

1910

1.55

6840

5.50

5700

- 3

15.1

22.5

840

1050

2090

1.45

600

5130

4.40

3940

- 8

8.5

17.4

740

930

1850

1.69

6840

5.30

5550

- 5

13.8

21.4

850

1060

2110

1.54

500

5000

3.30

3730

-20

5.2

13.0

450

560

1120

1.64

7500

4.10

6010

-17

10.8

17.5

630

800

1580

1.37

10000

5.10

8290

-13

16.3

22.2

740

920

1840

1.37

550

5000

3.20

3630

-21

4.6

12.3

410

520

1030

1.79

7500

3.90

5900

-19

9.8

16.5

610

760

1520

1.45

10000

4.90

8120

-15

15.0

21.0

730

910

1820

1.44

600

5000

3.20

3490

-22

4.0

11.8

380

480

950

2.01

7500

3.80

5770

-20

9.0

15.8

590

740

1460

1.54

10000

4.70

7980

-17

14.0

20.1

710

890

1760

1.52

500

5300

7.5

2.30

3940

-39

3.6

9.2

280

350

690

1.53

7070

2.60

5540

-38

6.2

11.5

380

470

950

1.35

10610

3.30

8710

-35

11.3

16.2

540

670

1340

1.32

14140

4.00

11900

-31

16.2

20.8

650

820

1630

1.36

550

7070

2.50

5450

-39

5.7

10.9

350

440

890

1.42

10610

3.20

8570

-36

10.5

15.4

510

640

1270

1.38

14140

3.90

11720

-33

15.3

19.9

620

780

1560

1.44

600

7070

2.50

5300

-39

5.2

10.3

330

410

820

1.51

10610

3.10

8450

-37

9.9

14.7

480

600

1200

1.45

14140

3.90

11500

-34

14.5

19.1

600

750

1490

1.51

* MEAN POINT OF IMPACT

4C-34-1-1—(219—5)

Figure 6-2 ID (Sheet 5 of 9)

Change 7 6-68AL

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

CBU-58/B or CBU-71/B DISPENSER and BOMB

3.0 G PULLOUT
.14 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI* OF FIRST AND

LAST CLUSTER

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BCMB

STICK

(FT)

BOMB

STICK

(FT)

500

3420

4.06

2520

- 7

4.2

15.0

820

1040

1890

2.21

5130

4.62

4180

- 5

10.6

19.0

1060

1340

2660

1.45

6840

5.88

5850

16.9

24.0

1120

1400

2800

1.38

550

5130

4.48

4060

- 7

9.4

18.1

1060

1330

2650

1.55

6840

5.46

5690

- 3

15.0

22.4

1170

1470

2930

1.45

600

5130

4.34

3950

- 8

8.4

17.4

1030

1290

2570

1.69

6840

5.32

S5S0

- 5

13.9

21.5

1180

1480

2950

1.54

500

5000

3.34

3720

-20

5.2

13.1

630

790

1570

1.64

7500

4.04

6030

-17

10.8

17.4

880

1110

2210

1.37

10000

5.02

8300

-13

16.2

22.1

1020

1280

2560

1.36

550

5000

3.20

3630

-21

4.5

12.3

580

720

1440

1.79

7500

3.90

5900

-19

9.8

16.5

850

1060

2130

1.45

10000

4.88

8120

-15

15.0

21.0

1020

1280

2540

1.44

600

5000

3.20

3490

-22

4.0

11.8

530

660

1330

2.01

7500

3.76

S780

-20

9.0

15.8

820

1020

2030

1.54

10000

4.74

7960

-17

14.0

20.1

990

1240

2470

1.52

500

5300

7.5

2.32

3930

-39

3.6

9.2

390

490

950

1.54

7070

2.66

5510

-38

6.2

11.5

530

660

1320

1.36

10610

3.36

8680

-34

11.3

16.2

750

940

1880

1.32

14140

4.06

11870

-31

16.2

20.8

910

1140

2280

1.36

550

7070

2.52

5440

-39

5.6

10.9

490

620

1220

1.42

10610

3.22

8560

-36

10.5

15.3

710

890

1780

1.38

14140

3.92

11700

-33

15.2

19.8

870

1090

2180

1.44

600

7070

2.52

5290

-39

5.1

10.3

460

570

1140

1.51

10610

3.08

8460

-37

9.8

14.7

670

840

1680

1.45

14140

3.92

11480

-34

14.5

19.1

840

1050

2090

1.51

* MEAN POINT OF IMPACT

4C—34-1 —1-(219—6)

6-68AM

Change 7

Figure 6-21D (Sheet 6 of 9)

T.O. 1F-4C-34-1-1

VIVE TOSS RIPPLE RELEASE j

' i

UHni

(CONnNUED)

CBU-58/B or CBU-71/B DISPENSER and BOMB

4.0 G PULim -
.06 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BCMB IN RIPPLE RELEASE

jjgg

WRCS

SETTM

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BCMB

STICK

(FT)

BCMB

STICK

(FT)

SOO

3420

3.24

2710

- 6

5.4

15.9

520

650

1300

1.92

5130

3.72

4400

- 3

11.9

20.2

610

760

1520

1.41

550

3420

3.24

2620

- 7

4.5

15.2

490

620

1220

2.23

5130

3.60

4300

- 5

10.7

19.2

610

780

1550

1.50

6840

4.38

5970

16.8

23.9

650

820

1630

1.44

600

3420

3.24

2530

- 8

3.7

14.6

440

560

1100

2.64

5130

3.48

4210

- 7

9.6

18.3

600

750

1510

1.62

6840

4.26

5850

- 3

15.5

22.9

670

830

1670

1.53

500

5000

2.74

3960

-19

6.0

13.7

380

480

950

1.57

7500

3.34

6310

-15

11.9

18.4

510

640

1280

1.36

10000

4.12

8660

-10

17.8

23.6

580

720

1440

1.36

550

5000

2.68

3860

-20

5.3

13.0

350

440

890

1.69

7500

3.22

6200

-17

10.8

17.5

500

630

1250

1.43

10000

3.94

8520

-13

16.3

22.2

580

730

1460

1.43

600

5000

2.62

3770

-22

4.7

12.4

330

410

820

1.85

7500

3.16

6080

-19

10.0

16.8

480

610

1200

1.52

10000

3.82

8390

-15

15.3

21.2

570

710

1420

1.51

500

5300

7.5

1.98

4140

-39

4.0

9.6

230

290

560

1.50

7070

2.20

5780

-37

6.7

12.0

310

390

780

1.34

10610

2.70

9070

-34

12.0

16.9

440

550

1090

1.31

14140

3.30

12330

-30

17.3

21.8

520

660

1310

1.35

550

5300

7.5

1.92

4050

-40

3.5

9.0

210

260

510

1.58

7070

2.16

5680

-38

6.1

11.3

290

370

730

1.40

10610

2.64

8940

-35

11.2

16.0

420

520

1040

1.37

14140

3.18

12190

-22

16.3

20.8

510

630

1260

1.43

600

7070

2.10

5590

-39

5.6

10.8

270

340

670

1.48

10610

2.60

8820

-36

10.5

15.4

390

490

980

1.44

14140

3.12

12040

-33

15.4

20.0

480

610

1210

1.51

* MEAN POINT OF IMPACT

4C-34-1-1-(219-7)

Figure 6-21D (Sheet 7 of 9)

Change 7

6-68AN

T.O. 1F-4C-34-1-1

CBU-58/B or CBU-71/B DISPENSER and BOMB

4.0 G PULLOUT
.10 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BOMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI* OF FIRST AND

LAST CLUSTER

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

500

3420

3.20

2720

- 6

5.3

15.8

850

1080

2140

1.92

5130

3.80

4390

- 2

12.1

20.4

1020

1270

2540

1.41

550

3420

3.20

2620

- 7

4.4

15.2

800

1020

2020

2.23

5130

3.60

4290

- 5

10.7

19.2

1030

1300

2570

1.50

6840

4.40

5970

16.8

23.9

1090

1360

2720

1.44

600

3420

3.20

2530

- 8

3.6

14.6

730

920

1830

2.65

5130

3.50

4200

- 7

9.6

18.4

1010

1270

2530

1.62

6840

4.20

5850

- 3

15.3

22.7

1110

1390

2770

1.53

500

5000

2.70

3970

-19

6.0

13.7

630

790

1580

1.56

7500

3.30

6320

-15

11.8

18.4

850

1070

2130

1.35

10000

4.10

8660

-10

17.7

23.5

960

1200

2390

1.36

550

5000

2.70

3860

-20

5.3

13.0

590

740

1490

1.70

7500

3.20

6200

-17

10.8

17.4

830

1050

2080

1.43

10000

3.90

8530

-13

16.3

22.2

970

1220

2420

1.43

600

5000

2.60

3780

-22

4.7

12.4

550

690

1380

1.85

7500

3.10

6100

-19

9.9

16.7

800

1000

1990

1.52

10000

3.80

8390

-15

15.2

21.2

950

1190

2370

1.51

500

5300

7.5

2.00

4130

-39

4.0

9.6

380

480

920

1.50

7070

2.20

5790

-37

6.7

12.0

520

650

1280

1.34

10610

2.70

9070

-34

12.0

16.9

730

910

1820

1.31

14140

3.30

12330

-30

17.2

21.8

870

1090

2180

1.35

550

5300

7.5

1.90

4070

-40

3.6

9.0

340

430

830

1.58

7070

2.10

5720

-38

6.1

11.3

480

610

1170

1.40

10610

2.60

8960

-35

11.1

16.0

690

870

1730

1.37

14140

3.20

12180

-32

16.2

20.8

840

1060

2110

1.43

600

7070

2.10

5590

-39

5.6

10.8

450

570

1100

1.48

10610

2.60

8810

-36

10.5

15.4

660

820

1640

1.44

14140

3.20

11990

-33

15.5

20.1

810

1010

2020

1.51

* MEAN POINT OF IMPACT

4C-34—l—l-(219-8)

6-68AP

Change 7

Figure 6-21D (Sheet 8 of 9)

T.O. 1F-4C-34-1-1

din TOSS RIPPLE RELEASE

CBU-58/B or CBU-71/B DISPENSER and BOMB

4.0 G PULLOUT
.14 SEC RELEASE INTERVAL
HOB - 1800 FT AGL

PICKLE CONDITIONS

MIDDLE BCMB IN RIPPLE RELEASE

DISTANCE BETWEEN

MPI* OF FIRST AND

LAST CLUSTER

WRCS

C B

SETTING

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

AGL

(FT)

SLANT
RANGE
(1000 FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGLE

(DEG)

CLUSTER

FUNCTION

TIME

(SEC)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STICK

(FT)

BOMB

STICK

(FT)

BCMB

STICK

(FT)

500

3420

3.18

2710

- 6

5.2

15.7

1180

1500

2960

1.93

5130

3.74

4390

- 3

11.9

20.2

1420

1780

3560

1.41

550

3420

3.18

2620

- 8

4.4

15.1

1100

1410

2800

2.25

5130

3.60

4290

- 5

10.6

19.2

1440

1810

3620

1.50

6840

4.44

5960

16.9

24.0

1520

1910

3800

1.44

600

3420

3.32

2510

- 8

3.7

14.7

1040

1350

2680

2.65

5130

3.46

4200

- 7

9.5

18.2

1400

1770

3520

1.62

6840

4.30

5840

- 3

15.5

22.9

1560

1950

3800

1.53

500

5000

2.78

3950

-19

6.0

13.8

890

1120

2240

1.57

7500

3.34

6310

-15

11.9

18.4

1200

1510

3000

1.36

10000

4.18

8650

-in

17.9

23.7

1350

1690

3360

1.36

550

5000

2.64

3880

-21

5.2

12.9

840

1060

2110

1.69

7500

3.20

6200

-17

10.8

17.4

1160

1470

2910

1.43

10000

3.90

8530

-13

16.3

22.1

1350

1700

3400

1.43

600

5000

2.64

3770

-21

4.7

12.4

780

980

1960

1.85

7500

3.20

6070

-18

10.0

16.8

1130

1420

2820

1.52

10000

3.76

8400

-15

15.2

21.1

1320

1660

3310

1.51

500

5300

7.5

2.04

4100

-38

3.9

9.6

530

660

1260

1.50

7070

2.24

S760

-37

6.7

12.0

730

910

1760

1.34

10610

2.80

9020

-33

12.0

16.9

1020

1280

2550

1.31

14140

3.36

12290

-30

17.3

21.8

1220

1530

30 60

1.36

550

5300

7.5

1.90

4070

-40

3.6

9.0

470

590

1120

1.58

7070

2.10

5710

-39

6.1

11.3

660

830

1600

1.40

10610

2.66

8920

-35

11.1

16.0

970

1210

2410

1.37

14140

3.22

12160

-32

16.2

20.8

1180

1480

2940

1.43

600

7070

2.10

5590

-39

5.6

10.7

620

780

1500

1.48

10610

2.65

8770

-36

10.5

15.4

920

1150

2290

1.45

14140

3.22

11980

-33

15.4

20.0

1130

1420

2820

1.51

* MEAN POINT OF IMPACT

4C-34-1-1—(219-9)

Figure 6-2 ID (Sheet 9 of 9)

Change 7

6-68AQ

T.O. 1F-4C-34-1-1

ME TOSS RIPPLE RELEASE

M36E2 INCENDIARY CLUSTER BOMB

2.0 G PULLOUT

0.10 SEC RELEASE INTERVAL
FUZE FUNCTION TIME - 6,0 SEC

PICKLE CONDITIONS

MIDDLE ROM? IN

RIPPLE RELEASE

DISTANCE
BETWEEN NPI*
OF FIRST AND
LAST CLUSTER

KNOTS

TAS

DIVE

ANGLE

(PEG)

ALT

AGL

(FT)

SLANT

RANGE

(FT)

PICKLE

RELEASE

-TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGIE

(DEG)

CLUSTER

FUNCTION

ALTITUDE

(FT)

TIME

RELEASE

IMPACT

(SEC)

BOMB

STTCK

(FT)

BOAT

STICK

(FT)

WRCS

Cg ^

SETTING

450

4000

11700

5.5

2860

- 9

1580

12.4

310

710

1.35

4500

13160

6.4

3260

- 7

2130

15.1

300

700

1.54

5000

14620

7.4

3680

- 5

2730

18.0

300

690

1.76

5500

16080

8.6

4130

- 2

3390

21.1

290

670

2.02

500

4000

11700

4.9

2800

-11

1260

10.7

310

730

1.30

4500

13160

5.7

3170

-10

1770

13.1

320

750

1.46

5000

14620

6.6

3550

- 8

2310

15.7

320

750

1.66

5500

16080

7.6

3950

- 6

2880

18.4

320

740

1.89

6000

17540

8.6

4380

- 4

3480

21.2

310

730

2.15

550

4000

11700

4.6

2720

-13

1000

9.5

310

730

1.27

4500

13160

5.2

3100

-12

1480

11.6

330

770

1.41

5000

14620

6.0

3460

-10

1970

13.9

340

790

1.58 ^

5500

16080

6.8

3830

- 9

2480

16.3

340

790

1.79

6000

17540

7.8

4200

- 7

3020

18.9

340

790

2.04

450

4500

9000

3.7

3170

-23

830

8.2

230

530

1.15

5000

10000

4.1.

3550

-22

1270

9.6

250

580

1.21

5500

11000

4.6

3900

-21

1700

11.1

260

610

1.29 ^ _,V

6000

12000

5.1

4260

-20

2140

12.9

280

640

1.40

6500

13000

5.6

4620

-19

2590

14.7

290

660

1.53

7000

14000

6.2

4970

-17

3040

16.6

290

680

1.68

500

5000

10000

3.8

3480

-24

960

8.4

240

550

1.19 .>

5500

11000

4.2

3840

-23

1380

9.8

260

600

1.26

6000

12000

4.6

4200

-22

1800

11.3

270

640

1.35

6500

13000

5.1

4540

-21

2220

12.9

290

670

1.46

7000

14000

5.6

4880

-20

2640

14.6

310

690

1.60

7500

15000

6.2

5210

-18

3060

16.4

310

710

1.75

550

5500

11000

3.9

3780

-24

1080

8.7

250

550

1.24

6000

12000

4.3

4120

-23

1480

10.7

270

620

1.32

6500

13000

4.7

4470

-22

1890

11.5

280

660

1.42

7000

14000

5.2

4790

-21

2290

13.1

300

690

1.54

7500

15000

5.7

5110

-20

2690

14.7

310

720

1.68

8000

16000

6.2

5440

-19

3100

16.3

310

740

1.83

450

6000

8490

3.0

4390

-39

950

7.8

180

410

1.14

6500

9190

3.2

4780

-38

1370

8.8

190

450

1.18

7000

9900

3.4

5180

-38

1780

9.9

210

480

1.23

7500

10610

3.7

5530

-37

2170

11.0

220

520

1.29 ✓

8000

11310

3.9

5930

-37

2590

12.3

230

550

1.37

500

6500

9190

3.0

4710

-40

990

7.8

180

420

1.17

7000

9900

3.2

5090

-39

1390

8.8

190

450

1.21

7500

10610

3.4

5480

-39

1780

9.9

210

480

1.26

8000

11310

3.6

5860

-38

2210

10.9

220

520

1.33

550

7000

9900

3.0

5030

-40

1050

7.9

180

420

1.21

7500

10610

3.2

5400

-40

1440

8.8

190

450

1.25

8000

11310

3.4

5780

-39

1840

9.8

210

490

1.30

* MPT - Mean Point of Impact

6-68AR

Change 7

Figure 6-21E (Sheet 1 of 4)

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

M36E2 INCENDIARY CLUSTER BOMB

2.0 G PULLOUT
0.10 SEC RELEASE INTERVAL
FUZE FUNCTION TIME - 7.0 SEC

PICKLE CONDITIONS

MIDDLE RON'S IN

RIPPLE RELEASE

DISTANCE
BETWEEN MPI*
OF FIRST AND
LAST CLUSTER

KNOTS

TAS

DIVE

ANGLE

(DEG)

ALT

ACL

(FT)

SLANT

RANGE

(FT)

PICKLE

RELEASE

TIME

(SEC)

RELEASE

ALTITUDE

(FT)

RELEASE

ANGIE

(DEG)

CLUSTER

FUNCTION

ALTITUDE

(FT)

TIM:

RELEASE

IMPACT

(SEC)

BON®

STTCK

(FT)

BON®

STICK

(FT)

WCS

r B

SETTING

4S0

4000

11700

5.3

2890

-10

1250

11.6

310

730

1.25

4500

13160

6.1

3300

- 8

1820

14.2

310

730

1.38

5000

14620

7.1

3700

- 5

2440

17.1

300

710

1.57

5500

16080

8.1

4150

- 3

3080

20.1

290

690

1.78

500

4000

11700

4.8

2820

-12

920

10.1

320

740

1.23

4500

13160

5.5

3200

-10

1440

12.3

330

770

1.33

5000

14620

6.3

3590

- 8

1990

14.8

330

770

1.48

5500

16080

7.2

3990

- 7

2560

17.5

330

760

1.67

6000

17540

8.2

4400

- 5

3180

20.3

320

750

1.89

550

4000

11700

4.5

2740

-13

640

9.0

310

730

1.22

4500

13160

5.1

3120

-12

1130

10.9

330

780

1.30

5000

14620

5.8

3490

-10

1630

13.1

340

800

1.43

5500

16080

6.5

3880

- 9

2150

15.4

350

810

1.59

6000

17S40

7.4

4250

- 7

2750

18.0

350

810

1.79

6500

19010

8.3

4650

- 6

3290

20.6

340

800

2.02

450

5000

10000

4.1

3550

-22

820

9.1

240

570

1.16

5500

11000

4.5

3930

-21

1270

10.5

260

610

1.21

6000

12000

4.9

4310

-20

1730

12.1

280

640

1.28

6500

13000

5.4

4670

-19

2180

13.8

290

670

1.38

7000

14000

5.9

5040

-18

2650

15.7

290

690

1.50

7500

15000

6.5

5400

-16

3120

17.6

300

700

1.63

500

5500

11000

4.1

3870

-23

920

9.3

240

590

1.20

6000

12000

4.5

4230

-22

1350

10.6

270

630

1.26

6500

13000

4.9

4600

-21

1790

12.1

290

670

1.34

7000

14000

5.4

4940

-20

2220

13.8

300

700

1.43

7500

15000

5.9

5290

-19

2660

15.5

310

720

l.SS

8000

16000

6.4

5650

-18

3110

17.3

310

730

1.69

550

6000

12000

4.2

4160

-23

1010

9.5

260

610

1.25

6500

13000

4.6

4510

-22

1420

10.8

280

650

1.31

7000

14000

5.0

4860

-22

1850

12.2

290

690

1.39

7500

15000

5.4

5220

-21

2270

13.8

310

720

1.50

8000

16000

5.9

5540

-20

2690

15.4

330

740

1.62

450

6500

9190

3.2

4780

-39

740

8.3

190

440

1.14

7000

9900

3.4

5180

-38

1160

9.3

200

470

1.17

7500

10610

3.6

5580

-38

1590

10.3

220

510

1.21

8000

11310

3.8

5980

-37

2010

11.4

230

540

1.26

500

7000

9900

3.2

5090

-39

740

8.3

190

440

1.17

7500

10610

3.3

5530

-39

1190

9.2

200

470

1.20

8000

11310

3.5

5920

-39

1600

10.2

220

500

1.24

550

7500

10610

3.2

5400

-39

760

8.3

190

440

1.21

8000

11310

3.3

5840

-40

1200

9.2

200

470

1.24

* MPI - Mean Point of Iinpact

4C-34-1-1—(218—2)

Figure 6-21E (Sheet 2 of 4)

Change 7

6-68AS

T.O. 1F-4C -34-1-1

M36E2 INCENDIARY CLUSTER BOMB

2.0 C RILT/XJT
0.10 SEC RELEASE INTERVAL

FUZE FUNCTION TIME - 8.(1 SET

piaaE conditions

MIDDLE BON® IN PIPPLE RELEASE

_ __——

DISTANCE
BETVEEN MPI*
OF FIRST AND
LAST CLUSTER

KNOTS

TAS

DIVE

ANGIE

(pf-g)_

ALT

AGL

(FT)

SLANT
RANGE
! (FT)

PICKLE

RELEASE

TINE

(SEC)

RELEASE

ALTITUDE

_1EQ_

RELEASE

ANGIE

(DEG)

CLUSTER

RUCTION

ALTITUDE

_CEQ_

TINE

RELEASE

REACT

(SEC)

BON®

STICK

_£m_

BON®

STICK

TOCS

r ®

SETTING

450

4000

11700

5.2

2900

-10

900

11.0

320

740

1.19

4500

13160

5.9

3320

- 8

1480

13.4

320

750

1.28

5000

14620

6.8

3730

- 6

2100

16.2

320

740

1.42

5500

16080

7.8

4160

- 4

2760

19.2

310

710

1.60

6000

17540

8.9

4620

- 1

3480

22.5

290

690

1.80

500

4500

13160

5.4

3220

-10

1090

11.6

340

780

1.26

5000

14620

6.1

3620

- 9

1640

14.0

340

790

1.36

5500

16080

6.9

4020

- 7

2220

16.6

330

790

1.51

6000

17540

7.8

4430

- 5

2840

19.4

330

770

1.69

6500

19010

8.8

4870

- 3

3500

22.3

330

730

1.89

550

4500

13160

5.0

3140

-12

750

10.3

340

780

1.26

5000

14620

5.6

3530

-11

1270

12.3

350

810

1.34

5500

16080

6.3

3910

- 9

1800

14.6

350

820

1.46

6000

17540

7.1

4290

- 8

2360

17.1

350

830

1.61

6500

19010

7.9

4690

- 6

2940

19.6

350

820

1.80

7000

20470

8.9

5100

- 5

3570

22.4

350

810

2.01

450

5500

11000

4.4

3960

-21

810

10.0

260

610

1.17

6000

12000

4.8

4340

.20

1280

11.4

280

650

1.22

6500

13000

5.2

4730

-19

1750

13.0

290

680

1.28

7000

14000

5.7

5100

-18

2220

14.8

300

690

1.37

7500

15000

6.2

5470

-17

2710

16.6

300

710

1.47

8000

16000

6.8

5830

-16

3200

18.6

310

720

1.60

500

6000

12000

4.4

4270

-22

870

10.1

270

630

1.21

6500

13000

4.8

4640

-21

1320

11.4

290

660

1.26

7000

14000

5.2

5010

-20

1770

12.9

300

700

1.33

7500

15000

5.6

5380

-20

2230

14.6

310

700

1.42

8000

16000

6.1

5730

-19

2680

16.3

320

740

1.52

550

6500

13000

4.5

4540

-23

940

10.2

260

640

1.26

7000

14000

4.8

4930

-22

1380

11.5

290

680

1.31

7500

15000

5.2

5290

-21

1810

13.0

310

710

1.38

8000

16000

5.6

5650

-20

2250

14.5

320

740

1.47

450

7500

10610

3.5

5630

-38

990

9.8

210

500

1.17

8000

11310

3.7

6030

-37

1410

10.8

230

530

1.20

500

8000

11310

3.5

5920

-39

930

9.7

210

500

1.21

* MPI

- Mean

Point of Impact

4C-34-l-l-(2)8^3)

Change 7

6-68AT

Figure 6-2 IE (Sheet 3 of 4)

T.O. 1F-4C-34-1-1

DIVE TOSS RIPPLE RELEASE

M36E2 INCENDIARY CLUSTER BOMB

4.0 G PULLOUT

PICKLE CONDITION

FUZE

FUNCTION

PICKLE TO
RELEASE

RELEASE

TIME

RELEASE

TAS

DIVE

ALT

ANG

ALT

TIME

TO IMPACT

SETTING

KTS

DEG

SEC

DEG

SEC

500

5000

2000

5.6

2.60

■1

-20

1.41

550

5000

2000

4.9

2.50

-21

1.49

500

-30

6000

2000

8.0

2.80

4954

-18

1.36

550

-30

6000

2000

2.70

4867

-20

1.42

500

-30

7000

2000

3.10

5877

-16

16.06

1.35

550

-30

7000

2000

3.00

5774

-18

15.11

1.40

500

-45

7000

2000

2.10

5774

-38

10.79

1.28

550

-45

7000

2000

5.8

2.10

5649

-38

10.10

1.32

500

-45

8000

2000

7.9

2.30

6669

-36

12.27

1.29

550

-45

8000

2000

7.2

2.20

6589

-38

11.48

1.32

500

-45

9000

2000

9.5

2.40

7591

-35

13.73

1.30

550

-45

9000

2000

8.7

2.40

7473

-36

12.88

1.34

4C-34- 1— 1 —(218—4)

Figure 6-21E (Sheet 4 of 4)

* U.s. GOVERNMENT PRINTING OFFICE: 1972-769-669/5012

Change 7

6-68AU/(6-68AV blank)

RELEASE ALTITUDE (AGL)-FEET

BLU-66/B(CBU-U/A)LEFT DEFLECTION

BLU-45/B CBU-33/A
IMPACT LATERAL VIS PLACEMENT

CBU-33/A MER TER SHOULDER POSITION CARRIAGE

RELEASE
DIVE ANCLE
DEG

RELEASE

ALTITUDE

RELEASE KTAS

1500

2000

4000

6000

2000

3000

4000

2000

3000

4000

5000

3500

4000

6000

8000

10000

12000

When the CBU-33/A is carried on the shoulder positions of either MERs or TERs, the BLU-45/B impact pattern will be displaced laterally
in the direction of the side ejection. The magnitude of this lateral displacement in feet is induced by an effective lateral munition ejection
velocity component of approximately 14 ft/sec (20 x sin 45°), as indicated in this tabulation. The lateral displacement distances listed are
measured from the point of ejection and includes the release conditions provided in the CBU-33/A bombing tables.

F4-34-VI-123

Figure 6-23

T.O. 1F-4C-34-1-1

BlU-49/B(CBU-38/A)IMPACTLATERAL DISPLACEMENT

CBU-38/A MER, TER SHOULDER POSITION CARRIAGE

RELEASE

DIVE ANGLE

DEG

RELEASE

RELEASE AIRSPEED

400KTAS

500KTAS

600KTAS

1000

229 FT

218 FT

207 FT

1500

279

263

249

2000

319

299

282

2500

352

330

311

3000

382

357

335

3500

409

381

357

4000

433

403

377

4500

455

423

396

5000

476

442

413

5500

496

460

429

6000

514

477

444

1500

195 FT

175 FT

158 FT

237

213

193

2500

272

246

224

3000

304

275

251

3500

332

301

276

4000

358

325

298

4500

382

347

319

5000

404

368

338

3000

245 FT

215 FT

191 FT

3500

273

240

214

4000

299

264

236

4500

323

287

257

5000

346

307

276

5500

367

327

295

6000

387

346

312

6500

406

336

329

7000

424

380

344

7500

441

398

359

8000

458

411

374

3500

233 FT

200 FT

175 FT

4000

258

223

196

4500

281

244

215

5000

304

264

234

5500

325

284

251

6000

344

302

268

6500

363

319

284

7000

382

336

300

7500

399

352

315

8000

416

368

329

8500

432

383

343

9000

447

397

357

9500

462

411

370

476

424

383

Note

WHEN THE CBU-38/A IS CARRIED ON THE SHOULDER POSITIONS OF EITHER MERS OR TERS, THE BLU-49/B IMPACT PATTERN WILL BE DIS¬
PLACED LATERALLY IN THE DIRECTION OF THE SIDE EJECTION. THE MAGNITUDE OF THIS LATERAL DISPLACEMENT IN FEET IS INDUCED
BY AN EFFECTIVE LATERAL MUNITION EJECTION VELOCITY COMPONENT OF APPROXIMATELY 44 FT/SEC (62 X SIN 45°), AS INDICATED IN
THIS TABULATION. THE LATERAL DISPLACEMENT DISTANCES LISTED ARE MEASURED FROM THE POINT OF EJECTION AND INCLUDE THE
RELEASE CONDITIONS PROVIDED IN THE CBU-38/A BOMBING TABLES.

F4-34-VI-124

Figure 6-24 ^

6-71(/6-72 blank;

T.O. 1F-4C-34-1-1

A/A

A/G

AGC

AGL

AGM

AIM

Aimpoint

Angle of Gun
Fire (AGF)

Antenna Train Angle

AOJ

API

ASE

Aspect Angle
Bezel

Blind Bombing
BLU

Bore Line (BL)

Boresighting

BST

CAS

CBU

CEP

DEP

Dog Bone

EOD

EWO

FFAR

Flight Path

Fire Bomb

FRL

Fuselage Angle of Attack
Fuselage Reference Line

GP Bomb
Ground Speed

Ground Track
Harmonization

HEAT

HOJ

HVAR

IAS

LABS

LAU

Launch Factor (F)

GLOSSARY

Air-to-Air

Aircraft Commander (front cockpit pilot). Formerly referred to as pilot.

Air-to-ground

Automatic Gain Control

Altitude above Ground Level

Air launched, Surface attack, guided missile.

Airborne Intercept

Air launched, Intercept-aerial, guided missile.

The preplanned point near or on the target that is used to align the pipper.

Usually this is a point that is offset from the target to correct for the wind
effect.

A px-efix to a Mark or Model designation to denote use by both Army/Air Force
and Navy

The angle formed between the timed barrel line and the aircraft flight path (or
relative airflow). The angle is used to determine trajectory shift.

The angle between interceptor heading and the bearing to the target.

Acquire-On-Jam
Armor Piercing Incendiary
Allowable Steering Error

The sum of Antenna Train Angle and Track Crossing Angle.

The scribes, marks, and numerals on the plastic overlay on the face of scope.
Bombing with the aid of radar and the WRCS Offset Bombing mode, without visual
reference to the target.

Bomb Live Unit

A line through a gun barrel bore extending to infinity.

See Harmonization
Bo resight

Knots Calibrated Airspeed. The airspeed read on the calibrated airspeed in¬
dicator when the Air Data Computer is operating properly.

Cluster Bomb Unit
Circular Error Probability
Centerline (Station 5)

Deflection (Cross Track) Error Probability

The Multiple Weapons Control Panel on the F-4C aircraft.

Explosive Ordnance Disposal

Electronic Warfare Officer

Folding Fin Aircraft Rocket

Aircraft attitude minus fuselage angle of attack.

Napalm, Anti-PAM (Personnel and Materiel), an incendiary munition.

Fuselage Reference Line.

The angle in mils between the aircraft flight path and the fuselage reference line.
The horizontal plane of the aircraft. The same as the water line, or the arma¬
ment datum line, or zero water line.

General Purpose bomb.

The speed of the aircraft relative to the ground. (True airspeed plus or minus
the rangewind component.)

The path or actual line of movement of the aircraft over the ground.

The adjustment (or boi-esighting) of the gun barrel so that, when the guns are
fired at the most effective range (2250 feet) the pipper will be on the bullet im¬
pact point.

High Explosive

High Explosive Anti-tank

Home-on-Jam

High Velocity Aircraft Rocket

Knots Indicated Airspeed, as read on the calibrated airspeed indicator when the
Air Data Computer is inoperative.

Identification Point, visual or radar
Infrared

Low Altitude Bombing System
Launcher Unit

A decimal value representative of rocket trajectory (a function of several vari¬
ables). The product of (F) and launcher line angle of attack represents the
angular l’otation of the rocket from the launcher line toward flight path (mils).

Glossary 1

T.O. 1F-4C-34-1-1

GLOSSARY (Cont)

Launcher Line (LL)

Launcher Line Angle
of Attack
LDGP
LI
LO

Line of Departure (LOD)
LOS

Mean Fixed Bore Line
(MFBL)

Mean Parallax

MER

MIL

Mod

MSEC

MSL

0/S

Parallax error
Passive Homing

Pickle

Pilot/WSO

Pipper

PLMS

PPI

Pressure Altitude
PSO

Pulse Length

Radar Boresight Line
(RBL)

Radar Mile

Radar Silence
RBL

Rehoming

REP

RIP

Semiactive Homing

Sight Depression from
Flight Path
Sight Picture
Sight Setting
Signal Strength
SUU
SW

Target Elevation

The projected longitudinal axis of the launching tube, or the CL of the rocket in
the tube.

The angle between the launcher line and relative airflow or aircraft flight path.

Low Drag General Purpose bomb.

Left Inboard (station 2).

Left Outboard (station 1)

The initial path of a projectile after firing. This includes trajectory shift but not
gravity drop.

Line of sight.

An average of all bore lines in a common gun system and extending to infinity.

The MFBL for gatling guns may also be defined as centerline of cluster.

When more than one gun is contained in a common system; mean parallax is the
average linear distance or separation between sight and guns.

Multiple Ejector Rack (Six ejector racks).

Milliradian. One mil=0.0573 degree. One degree=l7.45 mils. Approximately
one foot at 1000 feet.

Mark. A designation for model.

Mach Number
Modification

Milliseconds, one msee=0.001 second.

Mean Sea Level
Nautical Mile (6076.1 feet)

Over the Shoulder. The bomb is released at an angle greater than 90 degrees so
that the bomb will fall back onto the target.

The error induced by the horizontal and vertical distance between the optical
sight to gun, launcher, or bomb rack.

The missile guides upon energy waves transmitted by the target. The missile
does not transmit a signal that can be detected by the target, e.g., AIM-4D
and AIM-9 missiles.

The bomb release button, or the action of depressing the bomb release button.
The pilot in the aft cockpit (also Weapons System Officer)

The 2-mil diameter dot in the center of the optical sight reticle.

Probability of kill in percentage.

Power Level Mode Switching.

Plan Position Indicator

The altitude read on the pressure altimeter when set on 29.92 inches Hg.

Pilot Systems Operator, the pilot in the aft cockpit. Now referred to as PILOT.
The transmission time or on time of a pulse radar set measured in microsec¬
onds.

The position of the radar antenna when in BST (Boresight) and A/G (Air-to-
ground). Two degrees below the Fuselage Reference Line.

One radar mile equals 6000 feet. The radar mile is a unit of time (12.4 micro¬
seconds) that is required for one pulse of radar energy to be transmitted 6000
feet and be reflected back to the receiver.

The radar is not transmitting, but in standby.

Radar Boresight Line. Two degrees below the fuselage reference line.

The act of positioning the release pulse to the first loaded station.

Range Error Probability
Right Inboard (station 8)

Radar Identification Point
Right Outboard (station 9)

A guidance concept where a missile receives and homes on reflected energy
transmitted by the missile launching aircraft.

The optical sight depression value in mils minus fuselage angle of attack.

The relationship of the pipper position to the target.

The value in mils that the optical sight is depressed.

Level or size of the return on the radar scope.

Suspension and release Unit.

Sidewinder (AIM-9B)

The height of the target or IP above mean sea level (MSL).

Glossary 2

Change

T.O. 1F-4C-34-1-1

GLOSSARY (Cont)

TAS

TDD

TER

Timed Barrel Line
(TBL)

Track Crossing Angle
Tracking Index (TI)
Trajectory
Trajectory Shift (TS)

Velocity Jump

Video

VIP

WRCS

Zero Sight Line

Knots true Airspeed. Calibrated airspeed corrected for temperature and pres¬
sure.

Target Detecting Device

Triple Ejector Rack (Three ejector racks)

A line extending to infinity through the bore in a timed barrel position. This
line is used as a reference during gun/tracking index harmonization.

The angle between headings of the interceptor and the target.

Optical Sight Pipper

Flight path of a projectile/bomb from firing/release to impact.

The term used to define the amount of shift or angular rotation of a projectile
when the timed barrel line and aircraft flight path (relative airflow) are not
coincident.

The angle through which a x’ocket rotates - in the vertical plane - as it shifts into
the relative airflow. The magnitude of the angle determines the Line of De¬
parture (LOD), which is obtained by taking the product of the launch factor
(F) and the launcher line angle of attack.

Referring to the intelligence displayed on the radar scope.

Visual Identification Point

Weapons Release Computer Set.

When the optical sight is set on zero mils depression, the pipper line of sight
is pai'allel to the fuselage reference line, or a water line.

Glossary 3/(Glossary 4 blank)

T.O. 1F-4C-34-1-1

REFERENCE

AFM 50-3
AFM 127-100
TACM 55-4
T.O. 1F-4C-01
T.O. 1F-4C-1
T.O. 1F-4C-2-12
T.O. 1F-4C-2-14

T.O. 1F-4C-2-15
T.O. 1F-4C-2-16

T.O. 1F-4C-2-17

T.O. 1F-4C-2-18
T.O. 1F-4C-2-18A
T.O. 1F-4C-2-19
T.O. 1F-4C-2-20
T.O. 1F-4C-2-30
T.O. 1F-4C-5
T.O. 1F-4C-33-1-1
T.O. 1F-4C-33-1-2
T.O. 1F-4C -33-1-3

T.O. 1F-4D-2-19
T.O. 1F-4D-2-33
T.O. 1F-4D-33-1-1

T.O. 1F-4D-33-1-2

T.O. 5N1-3-15-2
T.O. 11-1-28

T.O. 11-1-29
T.O. 11-1-30
T.O. 11-1-31
T.O.11-1-32
T.O.11-1-33

T.O. 11A-1-1
T.O. 11A-1-10-11
T.O. 11A-1-10-33
T.O. 11A-1-55
T.O. 11A1-1-7
T.O. 11A1-1-12

T.O. 11A1-1-10-17
T.O. 11A1-4-2-7
T.O. 11A1-5-7-4

T.O. 11A1-5-8-1
T.O. 11A1-5-8-22

T.O. 11A1-5-12-2

Fighter Weapons (Training)

Explosives Safety Manual (Ground Safety)

F-4 Aircrew Operational Procedures

Model F-4, Series C (Depot Level), LOAD - F-4C, D,RF-4C
F-4C/D/E Flight Manual

Model F-4, Series C, Maint Instr - Air Data Computer Set - F-4C, D, RF-4C
Model F-4, Series C, Maint Instr - Integrated Electronic Central AN/ASQ-19
and Radar Altimeter AN/APN-155 - F-4C, D
Model F-4, Series C, Maint Instr - Navigation Sys - F-4C, D, RF-4C

Model F-4, Series C, Maint Instr - Automatic Fit Control Sys - F-4C, D,

RF-4C

Model F-4, Series C, Maint Instr - Attitude Reference and Bombing Computer
Sys - F-4C, D, RF-4C
Armament Systems

Model F-4, Series C - Suppl - Maint Instr - Armament Sys - F-4C, D, RF-4C
F-4C Fire Control System

Model F-4, Series C, Maint Instr - Airborne FCS (Maint Procedures) - F-4C

Model F-4, Series C, Field Maint Instr - Electronics Intelligence Sys - F-4C, D

Model F-4, Series C, Basic Wt Check List and Loading Data - F-4C Series
Conventional Munitions Basic Loading Information
Conventional Munitions Loading Procedures

Model F-4, Series C, Conventional Munitions Loading Procedures - Pre-MAU-
12B/A - F-4C, D
F-4D Fire Control System

Weapons Release Computer and Lead Computing Optical Sight System
Model F-4, Series D (Depot Level), Basic Information - Conventional Munitions
Loading Procedures - F-4D

Model F-4, Series D (Depot Level), Conventional Munitions Loading Procedures-
F-4D

Weapons Release Computer Set AN/ASQ-91

Armament Hazard Detecting and Personnel Ejection Sys and Associated Equip¬
ment Technical Orders - General - Bombs, Fins, Fuzes, Arming Wires and
Related Components
Tactical Munitions Manual for Bombs
Tactical Munitions Manual for Rockets and Missiles
Tactical Munitions Manual for Small-Arms Ammunitions
Tactical Munitions Manual for Dispensers and Bombs (CBU)

Armament, Fire Control Guidance, Hazard Detecting, Personnel Ejection Sys¬
tems and Associated Equipment Technical Orders - General Safety Require¬
ments - (Explosive)

Ammunitions, (Bombs and Fuzes) Restricted or Suspended
Ammunition Inspection Procedures - 20MM Electric Primed Ammunition
Ground Handling of Aircraft Containing Ammunition and Explosive Material
Fire Fighting and Withdrawal Time/Distance
Fuzes, General

Bombs for Aircraft: Bomb Demolition, 750 lbs., 754E2 (M117); 3000 lbs.

T55E16 (M118), 10,000 lbs. T56E4 (M121) with authorized Fuzes of Electrical
Impact Bomb, Demolition 750 lbs., Ml 17
Fuzes, Proximity
Bomb, Demolition 750 lbs., M117

Org Maint Repair Parts and Special Tool List - Dispenser and Bomb, Aircraft
CBU-1/A

Operation and Org Maintenance Manual - Dispenser and Bomb CBU-2/A
Field and Depot Maintenance Manual - Dispenser and Bomb Aircraft Type
CBU-3/A

Maintenance, Storage, and Inspection of Dispenser and Bomb, Aircraft:

CBU-7/A

Reference 1

REFERENCE (Cont)

T.O. 11A1-11-1-1
T.O. 11A5-8-1
T.O. 11A7-1-1
T.O. 11A7-1-7
T.O. 11A7-1-8
T.O. 11A7-6-7

T.O. 11A9-8-7

T.O. 11A10-1-1
T.O. 11A11-2-7

T.O. 11A13-4-7
T.O. 11A15-1-17
T.O. 11A15-1-157
T.O. 11AA12
T.O. 11B1-AJB7-2

T.O. 11C2-1-1
T.O. 11C2-i2-3-7
T.O. 1102^2-4-7
T.O. 1102-^2-4-7
T.O. 11L1-3-19-1
T.O. 11L1-I3-20-1

T.O. 11L1-3-21-1

T.O. 11L343-5-2

T.O. 11W1-31-2-2

T.O. llWl-31-5-2
T.O. 21M-AIM4-101
T.O. 21M-AIM4-103

T.O. 21M-AIM4A-01

T.O. 21M-AIM4D-2
T.O. 21M-AIM4D-4
T.O. 21M-AIM7D-01
T.O. 21M-AIM7D-2
T.O. 21M-AIM7D-2-1

T.O. 21M-AEM7D-102
T.O. 21M-AGM7D-103

T.O. 21M-AIM9B-2
T.O. 21M-AIM9B-101
T.O. 21M-AIM9B-105
T.O. 21M-AGM12-102
T.O. 21M-AGM12B-01

T.O. 21M-AGM12B-2

T.O. 21M-AGM12C-2
T.O. 21M-AGM45A-01
T.O. 21M-AGM45A-2

T.O. 21M-AGM45A-102

Storage, Handling, and Use-Leaflet Bomb - 750 pound M129 and M129E1.

SUU-7A/A Dispenser

Fuzes, Proximity

Fuzes, M905, M906

Fuzes, M907, M908, M909

Fuze, M910

Storage, Handling, Assembly, Inspection and Disposal Procedures - Land
Mine Type MLU-10/B
Military Pyrotechnics

Storage, Handling, and Inspection, Folding Fin Aircraft Rocket - 2.75 Inch and
Components.

Storage Handling and Inspection - 20MM Ammunition
Storage, Handling, and Inspection - AGM-12B (Bullpup) Missile
Storage, Handling, and Inspection - AGM-12B (Sidewinder) Missile
TDU-ll/B HVAR Target Rocket

Type AJB7 Series, Field Maint. Instr - Attitude Reference Bombing Sys, Type
AN/AJB-7 (Lear Siegler) - F-4C
Fuzes, General Chemical Bombs

Bomb Gas, Nonpersistent, GB, Bomb, 750 lb. Type MC-1
Fuze, FMU-7/B

Anti-Personnel and Material Bomb - BLU-l/B and BLU-lB/B, 750 Pound
Type LAU-34/A Opr and Main Instr - Launcher, Type LAU-34/A (Martin) - AGM-12A.
Type LAU-32A/A, LAU-32B/A, LAU-49/A Opr and Handling Instr for the
Rocket Launcher, LAU-32A/A, P/N 63A-112J5 (Commercial Manual) -
F-100, -104, -105, -111A T-28, B-57, F4C, A-1E
Type LAU-3/A Opr Instr - Rocket Launcher, Type LAU-3/A (Chromecraft
Company) - F-100, -104G, -105B, D, F, -111, F4C, F-5, A-lE, T-28, B-26
Part Number 462054-120, 462154-120, 462057-100, 462050-110, 462254-100,
Field Maint Instr - Airborne Missile Control Sub-System F4/AIM-4D
Type SUU-16/A, Field Maint Instr - Armament Pod, Model SUU-16/A, P/N
721E729G1 (Springfield Armory) - F-4C, F-100, F-105, F-lll
Type SUU-23/A, Field Maint Instr O/H - 20MM gun, Type SUU-23/A Pod
Air Launched, Intercept, Aerial; Operating Data - AIM-4A, C, D, F, G.

Air Launched, Intercept, Aerial; Temperature Capabilities - AIM-4A, B,

C, D, E, F.

Model AIM-4, Series A (Falcon), LOAP - Missiles and Equipment AIM-4A,

B, C, D, E, F, G

USAF Model AIM-4D (Falcon) Missiles Assembly, Service and Maintenance
Model AIM-4, Series D (Falcon), Illustrated Parts Breakdown - AIM-4D
Model AIM-7, Series D (Sparrow ni), LOAP - AIM-7D, E
Model AIM-7, Series D (Sparrow HI), Assy, Svc, and Maint Instr - AIM-7D/E
Model AIM-7, Series D (Sparrow III), Partial Manual - Assy, Svc and Maint
Instr - AIM-7D, -7E (Used with T.O. 21M-AIM-7D-2)

Model AIM-7, Series D (Sparrow HI), Operational Data - AIM-7D, -E
Model AIM-7, Series D (Sparrow III), Guidance and Control Unit and Test Re¬
sults - AIM-7D, E

Model AIM-9, Series B (Sidewinder), Org Maint Instr - AIM-9B
Model AIM-9, Series B (Sidewinder), Operational Data AIM-9
Model AIM-9, Series B (Sidewinder), Performance Manual - AIM-9B
Air Launched, Surface Attack, Operational Data - AGM-12B, C
Series B (Bullpup), (Depot Level), LOAP - Guided Missile and Equip - AGM-
12A/B

Series B (Bullpup) - (Depot Level), Assy, Checkout and Handling Instr -
AGM-12B

Series C (Bullpup) (Depot Level) - Assembly, Svc and Maint Instr - AGM-12C
Model AGM-45, Series A (Shrike) (Depot Level). LOAP AGM-45A
Model AGM-45, Series A (Shrike) - Assembly, Checkout, and Maint Instr - IPB-
Type I, Type III Training Missile - AGM-45A
Model AGM-45, Series A (Shrike), Operational Data - AGM-45A

Reference 2

T.O. IF-4C-34-1-1

ALPHABETICAL /HDEX

A/B 45Y-1 Liquid Agent Spray Tank. .
A/B 45Y-2 Dry Agent Spray Tank . . .
A/B 45Y-4 Dry Agent Spray Tank . . .
A/B 45Y-1, -2, -4 Spray Tanks. . . .
A/B 45Y-1, -2, -4 Spray Tank Dis¬
pensers (F-4C).

A/B 45Y-1, -2, -4 Spray Tank Dis¬
pensers (F-4D).

A/B 45Y-1, -2, -4 Spray Tank Dis¬
pensers (F-4E).

Activate Switch (F-4D).

Activate Switch (F-4E).

Adaptive Control System (F-4D). . . .
Adaptive Control System (F-4E). . . .
(ADI) Attitude Director Indicator . . .

AERO 3B Launcher (F-4E).

AERO-7A Launcher (F-4E).

AERO-7A Missile Launcher (AIM-

7D/E/E-2) F-4C.

AERO-7A Missile Launcher (F-4D) . .
AERO-27/A, BRU-5/A Bomb Rack

(F-4C).

AERO-27/A, BRU-5/A Bomb Rack

(F-4D).

AERO-27/A, BRU-5/A Bomb Rack

(F-4E).

AGM-12, Jettison Controls (F-4D) . .

AGM-12, Jettison Controls (F-4E) . .
AGM-12, Offset Deliveries (F-4D) . .
AGM-12, Roll Reference Shift (F-4D) .

AGM-12 Selection (F-4C).

AGM-12, Station Select Buttons

(F-4D).

AGM-12 Weapon System (F-4C). . . .
AGM-12 Weapon System (F-4D). . . .
AGM-12 Weapon System (F-4E). . . .

AGM-12B Missile (F-4C).

AGM-12B Missile (F-4D).

AGM-12B Missile (F-4E).

AGM-12B and -12C Fuze Triggering

Device.

AGM-12B and -12C Warhead and Fuze .

AGM-12B, C, E Missiles.

AGM-12B, C, E Missiles (F-4C) . . .
AGM-12B, C, E Missiles (F-4D) . . .
AGM-12B, C, E Missiles (F-4E) . . .

AGM-12C and -12E Missiles (F-4C). .

AGM-12C and-12E Missiles (F-4D). .
AGM-12C and-12E Missiles (F-4E). .

AGM-12E Fuze Triggering Device. . .

Page No.

Page No. A/G Missiles (F-4E). 1-112

AIM-4D Coolant Supply Mode (F-4D). . 1-50

AIM-4D Launcher (F-4E). 1-155

AIM-4D Missile Launchers (F-4D) . . 1-90

1-206 AIM-4D, -9 Missile Jettison (F-4E). . 1-146

1-207 AIM-4D Training Missile. 1-252

1-208 AIM-7 Missile Jettison (F-4E) .... 1-145

1- 206 Aircraft Weapon System Controls

(F-4C). 1-9

2- 7 Aircraft Weapon System Controls

(F-4D). 1-42

2-40 Aircraft Weapon System Controls

(F-4E) After T.O. 1F-4E-556 .... 1-114

2-76 Aircraft Weapon System Controls

(F-4E). 1-106

2-93 Airspeed. 5-29

1-80 Airspeed Conversion Chart. 5-4

1-143 Air Refueling Release (ARR) Button

1-94 (F-4D). 1-50

1-157 Air Refueling Release (ARR) Button

1-121 (F-4E). 1-121

1-155 Air-to-Air Gunnery (F-4D). 1-61

1-155 Air-to-Air Gunnery (F-4E). 1-123

Air-to-Air Weapons (F-4E). 1-114C

1-28 Air-to-Ground Lock-on (F-4D) .... 1-65

1-90 Air-to-Ground Lock-on (F-4E) .... 1-129

Air-to-Ground Weapons (F-4E) .... 1-114

1-26 Allowable CG Range. 4-12

Altimeter Lag Chart. 5-4

Altimeter Position Error. 5-4

Altitude Conversion Chart. 5-4

1-146A Ammunition Drum and Conveyor

1-97 System (F-4E). 1-125

1-160 Ammunition, 20mm. 1-167

1-96 (AN/ARW-77), Transmitter and Con-

1-96 trol Selector (F-4C). 1-30

1-33 (AN/ARW-77), Transmitter and Con¬
trol Selector (F-4D). 1-93

1-97 (AN/ARW-77), Transmitter and Con-

1-29 trol Selector (F-4E). 1-156

1-93 AN/AWM-19, Umbilical Test Set

1-156 (UTS). 1-250

1-29 Angle of Attack. 5-29

1-93 Angle of Attack Chart. 5-3

1-156 AN-M147A1 Mechanical Time Fuze . . 1-225

API, 20mm. 1-168

1-212 Armament Pylons (F-4C). 1-26

1-212 Armament Pylons (F-4D). 1-84

1- 210 Armament Pylons (F-4E). 1-146B

2- 9 Armament Safety Override Panel

2-43 (F-4C). 1-20

2-79, Armament Safety Override Panel

2-96 (F-4D). 1-81

1-29, Armament Safety Override Panel

1-212A (F-4E). 1-144

1-93, Arming Wire/Lanyard Routing .... 1-219

1-212A Arm Nose Tail Switch (F-4C). 1-48

1-156, Arm Nose Tail Switch (F-4D). 1-48

1-212A Arm Nose Tail Switch (F-4E). 1-107,

1-212 1-114B

Change 6 Index 1

T.O. 1F-4C-34-1-1

Page No.

Page No

(ARR) Button) Air Refueling Release

(F-4D). 1-50

(ARR) Buttonj Air Refueling Release

(F-4E). 1-121

Attitude Director Indicator (ADI)

(F-4C). 1-16

Attitude Director Indicator (ADI)

(F-4D). 1-59

Attitude Director Indicator (ADI)

(F-4E). 1-121

Automatic Acquisition Switch (F-4D). . 1-51

Aircraft Weapons Release Unit (AWRU)

F-4E. 1-114C

Aux Armament Control Panel (F-4D) . 1-80

Aux Armament Control Panel (F-4E) . 1-143

AWRU Operational Modes (F-4E) . . . 1-114C

(AWRU) Pairs - Manual. 1-114C

(AWRU) Pulse Width (F-4E). 1-114C

(AWRU) Salvo (F-4E). 1-114C

(AWRU) Single-Continuous (F-4E). . . 1-114C

(AWRU) Single-Manual (F-4E) .... 1-114C

(AWRU) Single-Ripple (F-4E). 1-114C

Ballistic Computer, CP-805/ASQ-91
(F-4D) . .. ; .

1-54

Ballistic Computer, CP-805/ASQ-91
(F-4E).

1-116

Ballistic Tables.

6-1

Ballistic Tables, Interpolation of . . .
Band Switch (F-4E).

5-3

1-111

BDU-33 Series Practice Bombs ....

1-248

BLU-l/B, B/|B, C/B Fire Bombs . . .

1-177

BLU-26/B Bomb.

1-186

BLU-31/B Dejmolition Bomb.

1-177,

BLU-36/B Bomb.

1-186A

BLU-39/B23 ^omblet.

1-187

BLU-39/B23 Bomb Package.

1-187

Bomb Rack BRU-5/A, (AERO-27/A)

F-4D.

1-83

Bomb Releas^ Angle Computer (F-4C).

1-16

Bomb Releas^ Angle Computer (F-4D).

1-60

Bomb Release Angle Computer (F-4E).

1-122

Bombing, Le[vel (F-4E).

1-102

Bombing, Lojft (F-4E).

1-105

Bombing, Ripple Release (F-4E) . . .

1-102

Bombing Tables.

5-9

Bombing Tabjles, MK 20 Mod 2, 3 . . .
Bombing Tinier (Dual Timer) (F-4C) .

1-191

1-18

Bombing Tinker (Dual Timer) (F-4D) .

1-60

Bombing Tinier (Dual Timer) (F-4E) .

1-122

Bombs & SUU-20 (F-4E).

2-85

Bombs, Practice.

1-248

Bombs Praciice, BDU-33 Series . . .

1-248

Bombs (F-4<i).

2-5

Bombs (F-4lb).

2-32

Bombs (F-4E).

2-68

Bombs/Ripple (F-4E).

1-112

Bombs/Single (F-4E).

1-112

Bombs/Tripjle (F-4E).

1-112

Boresight Mjethod.

4-7

BRU-5/A Bomb Rack AERO-27/A

(F-4C).

BRU-5/A Bomb Rack AERO-27/A

(F-4D).

BRU-5/A Bomb Rack AERO-27/A

(F-4E).

Built-In-Test (BIT) WRCS (F-4D) . . .
Built-In-Test (BIT), WRCS (F-4E) . .
BLU-45/B (CBU-33/A) Impact Lateral

Displacement.

BLU-49/B (CBU-38/A) Impact Lateral

Displacement.

BLU-52/B, A/B Chemical Bombs . . .

BLU-59/B Bomb.

BLU-61A/B Bomb.

BLU-66/B Bomb.

BLU-66/B (CBU-46/A) Left Deflec¬
tion .

BLU-76/B General Purpose Bomb. . .

Bomb Button (F-4C).

Bomb Button (F-4D).

Bomb Button (F-4E).

Bomb Button Transfer Relay (F-4C). .
Bomb Button Transfer Relay (F-4E). .

Bomb Delivery, Fire (F-4E).

Bomb Delivery, High Drag GP (F-4E) .
Bomb Delivery, Leaflet (F-4E) . . . .
Bomb Delivery, Low Drag (F-4E). . .
Bomb Dispenser, SUU-21/A (Modified)

F-4D.

Bomb Dispenser, SUU-21/A (F-4E) . .
Bomb Dispenser, Modified SUU-21/A
(F-4E).

Bomb/Fuze Compatability.

Bomb Fuzes.

Bomb Fuze Safety Features.

Bomb Fuzes, Classification of ... .

Bomb, MK 106 Practice.

Bomb Rack Adapter, Centerline
(F-4C).

Cage Functions (F-4E).

Cage Reset (F-4E).

Camera Control Panel.

Camera, Radar Scope.

Cameras, N-9 and DBM-4/KB-21. . .
Camera System, Combat Documenta¬
tion Motion Picture.

CBU and Flare Dispensers (F-4C). . .
CBU and Flare Dispensers (F-4D). . .
CBU and Flare Dispensers (F-4E). . .
CBU and Flare Dispensers (F-4E)

After T.O. 1F-4E-556 .

CBU Delivery.

CBU Delivery (F-4C).

CBU Delivery (F-4D).

CBU Delivery Using the SUU-7 Dis¬
penser (F-4C).

CBU Delivery Using the SUU-7 Dis¬
penser (F-4D).

1-26

1-83

1-146A

1-55

1-117

5-8

1-178

1-186A

1-179

5-8

1-178A

1-11

1-51

1-111

1-14

1-111

1-102

1-104

1- 104A
1-102

2- 44A
2-81

2-82,

2-97

1-163

1-217

1-219

1-248

1-26

1-114F

1-114G

1-252

1- 250,

2- 99
1-264A

1- 264A

2 - 6
2-38
2-73

2-90

1-102

1-6

1-38

1-6

1-40

Index 2

Change 6

T.O. 1F-4C-34-1-1

Page No.

CBU Delivery Using the SUU-7 Dis¬
penser (F-4E). 1-104

CBU Panel (F-4C). 1-14

CBU-1, -2, Series Weapons. 1-179

CBU-7A/A Dispenser and Bomb . . . 1-186A

CBU-12/A, A/A Dispensers and

Bombs. 1-184

CBU-24/B, A/B, B/B, C/B Dis¬
pensers and Bombs. 1-186

CBU-29/B, A/B, B/B, C/B Dis¬
pensers and Bombs. 1-186

CBU-30/A Dispenser and Bomb . . . 1-187

CBU-33/A Dispenser and Mine .... 1-190

CBU-34/A, A/A, -42/A Dispensers

and Mines. 1-190

CBU-38/A, A/A, (SUU-13A/A) Dis¬
pensers and Bombs. 1-188

CBU-46/A Dispenser and Bomb. . . . 1-179

CBU-52A/B Dispenser and Bomb . . . 1-186A

CBU-49/B, A/B, B/B, C/B Dis¬
pensers and Bombs. 1-186A

CBU-58/B Dispenser and Bomb. . . . 1-186

(Cb), WRCS Drag Coefficients .... 5-7

Centerline Bomb Rack Adapter (F-4C). 1-26

Centerline Bomb Rack Adapter (F-4D). 1-83

Centerline Bomb Rack Adapter (F-4E). 1-146A

Centerline Bomb Release (DCU-94/A) . 2-5

Centerline Station Jettison (F-4C). . . 1-19,

3-4

Centerline Station Jettison (F-4D). . . 1-81,

3-10

Centerline Station Jettison (F-4E). . . 1-144

Centerline Weapon Release (DCU-

94/A) F-4D Thru Blk 33. 2-36

Centerline Weapon Release (DCU-

94/A) F-4E. 2-72,

2-89

Chemical Bombs, BLU-52/B, A/B . . 1-178

Cluster Bomb, MK 20 Mod 2 and

Mod 3. 1-191

Cockpit Controls (Missiles) F-4C . . . 1-33

Combat Documentation Motion Picture

Camera System. 1-264A

Combat Support Equipment. 1-264

Combat Support Equipment (F-4E). . . 1-160A

Combat Weapons. 1-162

Computer Accuracy (WRCS). 4-9

Computer, Bomb Release Angle

(F-4C). 1-16

Computer, Bomb Release Angle

(F-4D). 1-60

Computer, Bomb Release Angle

(F-4E) . 1-122A

Computer Control Panel, Weapons
Release (F-4D)i. 1-54

Computer Control Panel, Weapons

Release (F-4E).

Computer, Flight Director Bombing

(F-4C).

Computer, Flight Director Bombing

(F-4D).

Computer, Flight Director Bombing

(F-4E) .

Computer Set, Weapons Release
(F-4D).

Page No.

Computer Set, Weapons Release

(F-4E). 1-114G

Control Panel, Multiple Weapons

(F-4C)... 1-9

Controls, Aircraft Weapon System

(F-4C). 1-9

Controls, Aircraft Weapon System

(F-4D). 1-42

Controls, Aircraft Weapon System
(F-4E) Before T.O. 1F-4E-556 . . . 1-106

Controls, Multiple Weapons (F-4C) . . 1-9

Conventional Weapon Suspension

(F-4C). 1-21

Converged vs. Parallel Fire. 4-8

Coolant Supply Mode, AIM-4D (F-4D) . 1-50

CTU-l/A Release Stability. 4-12

CTU-l/A Resupply Container. 1-266

Cursor Control Panel (F-4D). 1-55

Cursor Control Panel (F-4E). 1-117

Cursor Controls (F-4D). 1-55

Cursor Controls (F-4E). 1-117

DCU-94/A Control-Monitor. 1-247

Delivery Mode Selector (F-4E) .... 1-114

Delivery Mode Selector Panel (F-4D) . 1-42

Delivery Mode Selector Panel (F-4E) . 1-106

Demolition Bomb, BLU-31/B. 1-177

Description of Charts and Tables ... 5-3

Destructor, MK 36. 1-174

Determination of Fuze Safe Arming

Times. 5-7

Determination of Minimum Acceptable

Release Altitude. 5-6

Direct Bomb Mode (F-4D). 1-36

Direct Bomb Mode (F-4E). 1-100

Direct Delivery Mode (F-4D). 1-62

Direct Delivery Mode (F-4E). 1-128A

Dispenser and Bomb, CBU-7A/A . . . 1-186A

Dispenser and Bomb, CBU-30/A . . . 1-187

Dispenser and Bomb, CBU-52A/B . . 1-186A

Dispenser and Bomb, CBU-58/B . . . 1-186

Dispenser and Mine, CBU-33/A. . . . 1-190

Dispenser, Flare (SUU-42/A). 1-198

Dispenser Intervalometers. 1-243

Dispenser, SUU-13/A. 1-186A

Dispenser, SUU-13A/A. 1-186A

Dispenser, SUU-21/A Bomb. 1-246

Dispenser, SUU-21/A Bomb (F-4C) . . 2-11

Dispenser, SUU-21/A Bomb (F-4D) . . 2-44

Dispenser, SUU-25A/A. 1-191

Dispenser, SUU-25B/A. 1-194A

Dispenser, SUU-25C/A. 1-195

Dispenser, SUU-30/B. 1-185

Dispenser, SUU-30A/B. 1-186

Dispenser, SUU-30B/B. 1-186

Dispenser, SUU-30C/B. 1-186

Dispensers, A/B 45Y-1, -2, -4 Spray

Tank (F-4C). 2-7

Dispensers, A/B 45Y-1, -2, -4

Spray Tank (F-4D). -40

Dispensers, A/B 45Y-1, -2, -4

Spray Tank (F-4E). 2-76

Dispensers and Bombs, CBU-12/A,

A/A. 1-184

Change 6 Index 3

T.O. 1F-4C-3I4-1-1

Dispensers and Bombs, CBU-24/B,

A/B, B/B, jC/B.

Dispensers and Bombs, CBU-29/B,

A/B, B/B, jC/B.

Dispensers ahd Bombs, CBU-38/A,

A/A, (SUU-13A/A).

Dispensers and Bombs, CBU-49/B,

A/B, B/B, C/B.

Dispensers a)id Mines, CBU-34/A,

A/A, -42/A|.

Dispensers, Bomb and Rocket

(SUU-20/A, A/A\ .

Dispensers, CBU and Flare (F-4C) . .
Dispensers, CBU and Flare (F-4E) . .
Dispensers, CBU and Flare (F-4E)

After T.O. 1F-4E-556 .

Dispensers, |SUU-13.

Dispensers, SUU-20/A, A/A Bomb/

Rocket (F-^C).

Dispensers, SUU-20/A, A/A Bomb/

Rocket (F-4D).

Dispensers, SUU-20/A, A/A Bomb/

Rocket (F-^E).

Dispensers, jsUU-30..

Dispensers, ;SUU-36.

Dispensers, jsuU-38.

Dive and Low Level Bombing

Conditions.

Dive Angle Vs Distance Chart ....
Dive Bombing (F-4C).

Dive Bombinjg (F-4D).

Dive Bombing (F-4E).

Dive Bombing and Low Level Bombing

Sample Problem.

Dive Laydown (F-4E).

Dive Laydown Bombing Mode (F-4D). .
Dive Laydown Bombing Mode (F-4E). .

Dive Recovery Charts.

Dive Toss Bombing Mode (F-4D) . . .
Dive Toss Bombing Mode (F-4E) . . .
Dive Toss/Dive Laydown (F-4D) . . .
Dive Toss/Dive Laydown (F-4E) . . .

Drag Coefficient Control (F-4D). . . .
Drag Coefficient Control (F-4E). . . .

DRSC Panel.

(Dual Timer), Bombing Timer (F-4C) .
(Dual Timer), Bombing Timer (F-4D) .
(Dual Timer), Bombing Timer (F-4E) .
D Value.

ECM Pod Jettison (F-4C).

ECM Pod Jettison, Multi-Station

(F-4D).

ECM Pod Jettison, Multi-Station

(F-4E) .

ECM Pod Jettison (Station 9) F-4D . .
ECM Pod Jettison (Station 9) F-4E . .

Emergency Jettison (F-4C).

Emergency; Jettison (F-4D).

Index 4 Change 6

Page No.

1-186

1-188

1-186A

1-190

2-6

2-73

2-90

1- 186A

2 - 10

2-44

2-80

1-185

1-190

5-15

5-6

1-3,

4-4

1- 36,

4- 4
1-100

5- 11

2- 73,
2-91
1-68
1-132
5-3
1-64

1- 128A

2- 33
2 - 68 ,
2-85
1-55
1-117
1-252
1-18
1-60
1-122A
5-2

1-20

1-82

1-145

1-82

1-145

1-19

1-80

Page No.

Emergency Jettison (F-4E). 1-144,

3-17

Emergency Release Button, External

Stores (F-4C). 1-19

Emergency Release Button, External

Stores (F-4D). 1-80

Emergency Release Button, External

Stores (F-4E) . 1-144,

1-146

Emergency Release Procedures

(F-4C). 3-3

Emergency Release Procedures

(F-4D). 3 -9

Emergency Release and Jettison Pro¬
cedures (F-4E) After T.O. 1F-4E-

556. 3-19

Emergency Release and Jettison Pro¬
cedures (F-4E) Before T.O. 1F-4E-

556. 3-17

Error Analysis. 4-4

Evacuation, Fire Fighting and

(F-4C/D/E). 3-23

Exposure Time Chart ........ 5-8

External Stores Emergency Release

Button (F-4C). 1-19,

3-3

External Stores Emergency Release

Button (F-4D). 1-80

External Stores Emergency Release

Button (F-4E). 1-144,

1-146A

Extra Picture Switch, KB-18A ....

Filter Switch (F-4E). 1-111

Fin Assemblies, Fire/Chemical Bomb. 1-178

Fire Bomb Delivery (F-4C). 1-5

Fire Bomb Delivery (F-4D). 1-38

Fire Bomb Delivery (F-4E). 1-102

Fire Bombs, BLU-l/B, B/B, C/B . . 1-177

Fire/Chemical Bomb Fin Assemblies . 1-178

Fire Fighting and Evacuation (F-4C/

D/E). 3-23

Flare Delivery, LUU-l/B, -5/B,

-6/B. 1-196

Flare Dispensing (F-4C). 1-7

Flare Dispensing (F-4D). 1-40A

Flare Dispensing (F-4E). 1-104B

Flare Dispensing Tables. 5-11

Flare, LUU-2/B. 1-196

Flare, MK 24 Mod 4. 1-196

Flare, MLU-32/B99 (Briteye) .... 1-197

Flares, Liquid Engine and Tracking . . 1-213

Flares, LUU-l/B, -5/B, -6/B Target

Marker. 1-195

Flechette, WDU-4A/A Warhead. . . . 1-205

Flight Director Bombing Computer

(F-4C). 1-16

Flight Director Bombing Computer

(F-4D). 1-60

Flight Director Bombing Computer
(F-4E). 1-122

T.O. 1F-4C-34-1-1

Page No.

FMU-7 Series Fuzes and Initiators . . 1-238

FMU-26A/B, B/B Fuzes. 1-227

FMU-26A/B, -26B/B Electric Time

Fuze. 1-186

FMU-30/B Nose Fuze. 1-232

FMU-54/B Tail Fuze. 1-241

FMU-56/B, A/B, B/B Proximity

Fuzes. 1-186

FMU-56/B Proximity Fuze. 1-234B

FMU-56A/B Proximity Fuze. 1-235

FMU-56B/B Proximity Fuze. 1-237

FMU-72/B Long Delay Fuze. 1-232

FMU-81/B Functional Description . . . 1-234A

FMU-81/B Short Delay Fuze. 1-234

Fold-Down Optical Sight (F-4C) . . . . 1-14

Freeze Button (F-4E). 1-118

Fuze, AN-M147A1 Mechanical Time. . 1-225

Fuze Arming. 5-6

Fuze Arming and Safe Escape. 5-6

Fuze Extenders. 1-242

Fuze, FMU-26A/B, -26B/B Electric

Time. 1-186

Fuze, FMU-30/B Nose. 1-232

Fuze, FMU-54/B Tail. 1-241

Fuze, FMU-56/B Proximity. 1-234B

Fuze, FMU-56A/B Proximity. 1-235

Fuze, FMU-56B/B Proximity. 1-237

Fuze, FMU-72/B Long Delay. 1-232

Fuze, FMU-81/B Functional Descrip¬
tion . 1-234A

Fuze, FMU-81/B Short Delay. 1-234

Fuze, MK 176 (PD). 1-205

Fuze, MK 178 (PD). 1-205

Fuze, MK 181 Point Initiating - Base

Detonating. 1-206

Fuze, MK 339 Mod 0 Mechanical

Time Nose. 1-224

Fuze, M427. 1-205

Fuze, M904E1/E2/E3 Nose. 1-224

Fuze, M905 Tail. 1-237

Fuze, M907 Mechanical Time .... 1-186,

1-225

Fuze Safe Arming Time Required ... 5-7

Fuze Safety Features. 1-219

Fuze Triggering Device (AGM-12B

and -12C). 1-212

Fuze Triggering Device (AGM-12E) . 1-212

Fuze, WDU-4A/A (Flechette). 1-206

Fuzes and Initiators, FMU-7 Series. . 1-238

Fuzes, Bomb. 1-217

Fuzes, Bomb Classification of ....

Fuzes, FMU-26A/B, B/B. 1-227

Fuzes, FMU-56/B, A/B, B/B Prox¬
imity . 1-186

Fuzes, Nose. 1-224

Fuzes, Tail. 1-237

Fuzes, 2.75-Inch Rocket. 1-205

Gas Bomb, MC-1. 1-172

GAM-Auxiliary Switch (F-4C). 1-10,

1-34

G-Loading. 4-6A

Gravity Drop (F-4D). I- 62

Page No.

Gravity Drop (F-4E). 1-123

Ground Fire Method. 4-8

Guided Bombs, Laser MK 84 and

Ml 18. 1-213

Gun Controls, Nose (F-4E). 1-127

Gun Electrical Control (F-4E) .... 1-125

Gun Firing (F-4C). 1-5

Gun Firing (F-4D). 1-36

Gun Firing (F-4E). 1-100

Gunnery, Air-to-Air (F-4D). 1-61

Gunnery, Air-To-Air (F-4E). 1-123

(Gunnery) Wingspan vs. Range (F-4E) . 1-128A

Gun Pod Controls (F-4C). 1-15

Gun Pod Harmonization. 1-165

Gun Pod, SUU-16/A, -23/A (F-4C) . . 2-9

Gun Pod, SUU-16/A, -23/A (F-4D) . . 2-42

Gun Pod, SUU-16/A, -23/A (F-4E) . . 2-77

Gun Pod, SUU-16/A, -23/A (F-4E)

After T.O. 1F-4E-556 . 2-95

Gun Pods. 1-162

Gun Purge System (F-4E). 1-125

Gun Select Controls (F-4E). 1-127

Gun Station Selector Switches (F-4C) . 1-15

Guns and Stores Switch (F-4D) .... 1-49

Guns and Stores Switch (F-4E) .... 1-110

Guns Clear Switch (F-4C). 1-15

Guns Clear Switch (F-4D). 1-49

Guns Clear Switch (F-4E). 1-110

Guns (F-4E). 1-112

Guns/Missile Switching (After

T.O. 1F-4E-556) F-4E. 1-128A

Guns/Missile Switching (Before

T.O. 1F-4E-556) F-4E. 1-128

Guns/Missile Weapon Select (F-4E) . . 1-114F

Guns Station Select And Arm (F-4E). . 1-114F

Gun (Station) Selector, Nose (F-4E) . . 1-127

Gun System, M61A1, Nose (F-4E). . . 1-125

Gyro Switch (F-4D). 1-80

Gyro Switch (F-4E). 1-143

Harmonization (Gun Pod). 1-165

Harmonization of Aircraft Guns .... 4-7

Heat Missile Jettison (F-4D). 1-83

Heat Missiles (F-4E).. 1-146A

HEI, 20mm. 1-168

High Drag G.P. Bomb Delivery (F-4C). 1-6A

High Drag G.P. Bomb Delivery (F-4D). 1-40

High Drag G.P. Bomb Delivery (F-4E) . 1-104

Hung Ordnance (F-4C). 3-3

Hung Ordnance (F-4D). 3-9

Hydraulic Drive Assemblies (Nose
Gun) F-4E. 1-125

Igniter, M23 or AN-M23A1. 1-240

Impact Distance, Side Ejection .... 5-4

Impact Pattern for Ripple Release. . . 5-2

Impact Velocity Tables. 5-7

Inboard Wing Station (Missile Jettison

Selector) F-4C. 1-19

Inboard Wing Station (Missile Jettison
Selector) F-4D. 1-81

Change 6 Index 5

T.O. 1F-4C-34-1-1

Page No.

Inboard Wing Station (Missile Jettison

Selector) F-4E. 1-144

Incendiary Cluster Bomb, M36E2 . . . 1-190

Inflight Considerations. 5-29

Inflight Procedures for Bombing Range

Selected Weapons (F-4C). 2-13

Inflight Procedures for Bombing
Range Selected Weapons (F-4D) . . . 2-47

Inflight Procedures for Bombing
Range Selected Weapons (F-4E) . . . 2-83

Inflight Procedures for Bombing
Range Selected Weapons (F-4E) After

T.O. 1F-4E-556 . 2-98A

Interpolation of Ballistic Tables .... 5-3

Intervalometer Step Switch (F-4C). . . 1-33

Intervalomete'rs, Dispenser. 1-243

Interval Switch (F-4C). 1-11

Interval Switch (F-4D). 1-49

Interval Switch (F-4E). 1-110

Jettison, A1M-4D, -9 Missile (F-4E) . 1-146

Jettison, AIM-7 Missile (F-4E) . . . 1-145

Jettison and Release, Nuclear Stores

(F-4C). 1-20

Jettison and Release, Nuclear Stores

(F-4D). 1-81

Jettison and Release, Nuclear Stores

(F-4E). 1-144

Jettison and Release Procedures,

Emergency (F-4E) After T.O. 1F-

4E-556 . 3-19

Jettison and Release Procedures,

Emergency (F-4E) Before T.O. 1F-

4E-556 . 3-17

Jettison, Centerline Station (F-4C) . . 1-19

Jettison, Centerline Station (F-4D) . . 1-81

Jettison, Centerline Station (F-4E) . . 1-144

Jettison Controls (AGM-12) F-4D . . . 1-97

Jettison Contijols (AGM-12) F-4E ... 1-160

Jettison Controls (F-4C). 1-19

Jettison Controls (F-4D). 1-80

Jettison Contijols (F-4E) After T.O.

1F-4E-556 . 1-146A

Jettison Controls (F-4E) Before T.O.

1F-4E-556 . 1-144

Jettison, ECM Pod (F-4C). 1-20

Jettison, Emergency (F-4C) . . r . 1-19

Jettison, Emergency (F-4D). 1-80

Jettison, Emergency (F-4E). 1-144

Jettison, Heal; Missile (F-4D). 1-83

Jettison, Missile (F-4D). 1-83

Jettison, Missile (F-4E). 1-145

Jettison, Missile (Inboard Wing and
Fuselage Stations) F-4C. l_ 2 i

Jettison, Multi-Station ECM Pod

(F-4D) . . 1. 1-82

Jettison, Multi-Station ECM Pod

(F-4E) . .. 1-145

Jettison, Outboard Station (F-4C) . . . 3-5

Jettison, Outboard Wing Station (F-4C). 1-20

Jettison, Outboard Wing Station (F-4D). 1-81

Jettison, Outboard Wing Station (F-4E). 1-144

Page No.

Jettison, Outboard Station Selective
(After T.O. 1F-4-863) F-4C . . . . . 1-20

Jettison, Outboard Station Selective

(After T.O. 1F-4-863) F-4D. 1-81

Jettison Procedures (F-4C). 3-3

Jettison Procedures (F-4D). 3-9

Jettison, Radar Missile (F-4D) .... 1-83

Jettison, Selective (F-4C). 1-19

Jettison, Selective (F-4E). 1-144,

1- 146

Jettison Selector Missile, Inboard

Wing Station (F-4D). 1-81

Jettison Selector (Missile), Inboard

Wing Station (F-4E). 1-144

Jettison Station 9, ECM Pod (F-4D) . . 1-82

Jettison, Station 9 ECM Pod (F-4E) . . 1-145

Jettison, Wing and CL Station (F-4E) . 1-146

KB-18A Extra Picture Switch.

KB-18A Strike Camera System .... 1-264

Kinematic Lead (F-4D). 1-62

Kinematic Lead (F-4E). 1-123

KMU-351/B and KMU-370/B Laser
Bomb Guidance Kits. 1-213

LABS/Offset Bomb/Tgt Find (F-4D). . 2-35

LABS/Offset Bomb/Tgt Find (F-4E). . 2-70,

2- 87

LABS/WRCS Bombing Modes (F-4E) . 1-141

Landing Gear Control Handle (F-4C) . 1-20

Landing Gear Control Handle (F-4D) . 1-81

Landing Gear Control Handle (F-4E) . 1-144

Laser Bomb Guidance Kits (KMU-

351/B and KMU-370/B). 1-213

Laser Guided Bombs (MK 82, MK 84,

M-118). 1-213

Launcher, AERO 3B (F-4E). 1-155

Launcher, AERO-7A (F-4D). 1-89

Launcher, AERO-7A (F-4E). 1-155

Launcher (AGM-12B Carriage), LAU-

34/A (F-4C). 1-29

Launcher (AGM-12B Carriage), LAU-

34/A (F-4D). 1-93

Launcher, AIM-4D (F-4E). 1-155

Launcher, LAU-3/A Rocket. 1-199

Launcher, LAU-7A/A (F-4E). 1-155

Launcher, LAU-34/A (AGM-12B

Carriage) F-4E. 1-156

Launcher, LAU-34/A (F-4C). 1-26

Launcher, LAU-34/A (F-4D). 1-84

Launcher, LAU-34/A (F-4E). 1-151

Launcher, RMU-8/A Reel. 1-256

Launchers, AIM-4D Missile (F-4D) . . 1-90

Launchers, Missile. 1-155

LAU-3/A Rocket Launcher. 1-199

LAU-7A/A Launcher (F-4E). 1-155

LAU-32, -59, -68 Rocket Launchers . 1-200

LAU-34/A Launcher (AGM-12B
Carriage). 1-29

Index 6

Change 6

T.O. 1F-4C-34-1-1

Page No.

LAU-34/A Launcher (AGM-12B

Carriage) (F-4D). 1-93

LAU-34/A Launcher (AGM-12B

Carriage) (F-4E). 1-156

LAU-34/A Launcher (F-4C). 1-26

LAU-34/A Launcher (F-4D). 1-84

LAU-34/A Launcher (F-4E). 1-151

Laydown (F-4D). 2-33

Laydown (F-4E). 2-69,

2-74,

2-86,

2-91

Laydown Bombing Mode (F-4D) .... 1-69

Laydown Bombing Mode (F-4E) .... 1-133

LDGP Bombs, MK82, MK83, MK84 . . 1-174

Lead Computing Optical Sight (F-4D) . 1-56

Lead Computing Optical Sight (F-4E) . 1-118

Leaflet Bomb Delivery (F-4C) .... 1-7

Leaflet Bomb Delivery (F-4D) .... 1-40A

Leaflet Bomb Delivery (F-4E) .... 1-104A

Leaflet Bomb, M129E1, E2. 1-173

Left Main Gear Scissors Switch

(F-4C). 1-20

Left Main Gear Scissors Switch

(F-4D). 1-81

Left Main Gear Scissors Switch

(F-4E). 1-144

Level Bombing (F-4C). 1-5

Level Bombing (F-4D). 1-38

Level Bombing (F-4E). 1-102

Level Bombing Table (Leaflet Bomb) . 5-9

Liquid Agent Spray Tank, A/B 45Y-1 . 1-206

Liquid Engine and Tracking Flares . . 1-212A

Lock-On, Air-to-Ground (F-4D) . . . 1-65

Lock-On, Air-to-Ground (F-4E) . . . 1-129

Loft Bombing (F-4C). 1-8

Loft Bombing (F-4D). 1-40A

Loft Bombing (F-4E). 1-105

Loft Bombing Controls (F-4C) .... 1-16

Loft Bombing Equipment (F-4E) . . . 1-121

Loft Bombing Equipment Controls

(F-4D). 1-59

Loft Bombing-Ripple Release (F-4E) . 2-71,

2-89

Loft Bombing Ripple Release Condi¬
tion . 5-22

Loft Bombing Sample Problem .... 5-22

Loft Bombing Tables. 5-10

Loft Bombing Wind Correction .... 5-8

Low Drag Bomb Delivery (F-4C) . . . 1-5

Low Drag Bomb Delivery (F-4D) . . . 1-38

Low Drag Bomb Delivery (F-4E) . . . 1-102

Low Level Bombing Error Analysis . . 4-5

LUU-l/B, -5/B, -6/B Flare Delivery. 1-196

LUU-l/B, -5/B, -6/B Target Marker

Flares. 1-195

LUU-2/B Flare. 1-196

Master Arm Switch (F-4C). 1-10

Master Arm Switch (F-4D). 1-42

MAU-12B/A Armament Pylons
(F-4C). 1-26

Page No.

MAU-12B/A, C/A Armament Pylons

(F-4D). 1-84

Maximum Fragment Envelope Charts . 4-1

Maximum Pull-Out-Altitude (Pickle

Alt). 4-9

Maximum Release Altitude. 4-9

MC-1 Gas Bomb. 1-172

MERS and TERS Rehoming (F-4C) . . 1-27

MERS and TERS, Rehoming (F-4D) . . 1-84

MERS and TERS, Rehoming (F-4E) . . 1-151

MER, Multiple Ejector Rack (F-4C). . 1-26

MER, Multiple Ejector Rack (F-4D). . 1-84

MER, Multiple Ejector Rack (F-4E). . 1-150

Minimum Pull-Out Altitude. 4-9

Mission Conditions. 5-11

Mission Description (F-4C). 1-3

Mission Description (F-4D). 1-36

Mission Description (F-4E). 1-100

Mission Planning Form. 5-3

Missile, AGM-12B (F-4C). 1-29

Missile, AGM-12B (F-4D). 1-93

Missile, AGM-12B (F-4E). 1-156

Missile, AIM-4D Training. 1-252

Missile Control (F-4C). 1-30

Missile Control (F-4D). 1-94

Missile Control (F-4E). 1-157

Missile Jettison (F-4D). 1-82

Missile Jettison (F-4E). 1-145

Missile Jettison (Inboard Wing and

Fuselage Stations) F-4C. 1-21

(Missile Jettison Selector), Inboard

Wing Station (F-4C). 1-19

Missile Launcher, AERO-7A (AIM-

7D/E/E-2) F-4C. 1-28

Missile Launchers. 1-155

Missile Station Select and Arm (F-4E). 1-114F

Missiles, A/G (F-4E). 1-112

Missiles, AGM-12B, C, E (F-4C). . . 2-9,

1-210

Missiles, AGM-12B, C, E (F-4D) . . 2-43,

1-210

Missiles, AGM-12B, C, E (F-4E) . . 2-79,

1-210

Missiles, AGM-12B, C, E (F-4E)

After T.O. 1F-4E-556 . 2-96,

1-210

Missile, AGM-12C and -12E. 1-213

Missiles, AGM-12C and -12E (F-4C) . 1-29

Missiles, AGM-12C and -12E (F-4D) . 1-93

Missiles, AGM-12C and -12E (F-4E) . 1-156

(Missiles), Cockpit Control (F-4C) . . 1-33

Missiles, Heat (F-4E). 1-146

MK 1 Warhead (HE). 1-202

MK 5 Warhead (HEAT). 1-202

MK 20 Mod 2, 3 Bombing Tables . . . 1-191

MK 20 Mod 2 and Mod 3 Cluster Bomb. 1-192

MK 24 Mod 4 Flare. 1-196

MK36 Destructor. 1-174

MK82 (Snakeye 1) and M117R High/

Low Drag Option, In-Flight Selec¬
tivity (F-4C). 1-6A

MK82 (Snakeye 1) and M117R High/

Low Drag Option, In-Flight Selec¬
tivity (F-4D). 1-40

Change 6 Index 7

T.O. IF-4C-34-1-1

Page No.

MK82 (Snakeye 1) and M117R High/

Low Drag Option, In-Flight Selec¬
tivity (F-4E). 1-104

MK82 (Snakeye 1) GP Bomb. 1-174

MK82, MK83, MX84 LDGP Bombs . . 1-174

MK 82, MK 84, M-118 Laser Guided

Bombs . L. 1-213

MK 106 Practice Bomb. 1-248

MK176 Fuze (PD). 1-205

MK178 Fuze (PD). 1-205

MK 181 Fuze (Point Initiating - Base

Detonating). 1-206

MK 339 Mod 0 Mechanical Time Nose

Fuze. 1-224

MLU-32/B99 Flare (Briteye). 1-197

MLU-32/B99 Flare (Briteye) Level

Release Table. 5-11

Modified A/A 37U-15 Tow Target

System (f/4C). 2-12)

1-262

Modified A/A 37U-15 Tow Target

System (F*4D). 2-46

Modified A/A 37U-15 Tow Target

System (F-4E). 2-82

Modified A/A 37U-15 Tow Target
System (F-4E) After T.O. 1F-4E-556. 2-98

Multiple Ejector Rack (MER) F-4C . . 1-26

Multiple Ejector Rack (MER) (F-4D). . 1-84

Multiple Ejector Rack (MER) (F-4E). . 1-150

Multiple Weapons Control Panel

(F-4C). 1-9

Multiple Weapons Controls (F-4C), . . 1-9

Multi-Station ECM Pod Jettison

(F-4D). 1-82

Multi-Station ECM Pod Jettison

(F-4E). 1-145

M-l Fuze Extenders. 1-242

M23 or AN-M23A1 Igniter. 1-240

M36E2 Incendiary Cluster Bomb . . . 1-190

M61A1, No^e Gun System (F-4E) . . . 1-125,

2-78

M61A1 Nose Gun (F-4E) After T.O.

1F-4E-556 .

M117R And MK82 (Snakeye 1) High/

Low Drag Option, In-Flight Selec¬
tivity (F-4C).

M117; MK 82, 83 LDGP; and MC-1

Bombs ..

M117R and MK82 (Snakeye 1) High/

Low Drag Option, In-Flight Selec¬
tivity (F-4D).

M117R and MK82 (Snakeye 1) High/

Low Drag Option, In-Flight Selec¬
tivity (F-4E).

M117D Destructor.

Ml 17 General Purpose (GP) Bomb.

M117R (Retarded) GP Bomb . . .

M118 General Purpose (GP) Bomb
M129E1, E2 Leaflet Bomb ....

M151 Warhead (PMI).

Ml56 Warhead (WP).

M339 Mod 0 Mechanical Time Nose

Fuze . . .

M427 Fuz^.

M904E1/E2/E3 Nose Fuze ....

M905 Tail Fuze. 1-237

M907 Mechanical Time Fuze. 1-186)

1- 225
N

Normal Release Sequence (F-4C) . . . 1-9

Nose Gun Controls (F-4E). 1-127

Nose Fuze, M339 Mod 0 Mechanical

Time. 1-191

Nose Fuzes. 1-224

(Nose Gun) Hydraulic Drive Assem¬
blies (F-4E). 1-125

(Nose Gun) Scavenge System (F-4E) . . 1-125

Nose Gun (Station) Selector (F-4E) . . 1-127

Nose Gun, M61A1 (F-4E). 1-78

Nose Gun, M61A1 (F-4E) After T.O.

1F-4E-556 . 2-96

Nose Gun System, M61A1 (F-4E) . . . 1-125

Nuclear Stores Release and Jettison

(F-4C). 1-20

Nuclear Stores Release and Jettison

(F-4D). 1-81

Nuclear Stores Release and Jettison

(F-4E). 1-144

N-9 and DBM-4/KB-21 Cameras . . . 1-264A

Offset Aimpoint. 5-5

Offset Bombing Mode (F-4D). 1-70

Offset Bombing Mode (F-4E). 1-134

Offset Bombing/Target Finding (F-4D). 2-34

Offset Bombing/Target Finding (F-4E). 1-92,

2- 69,

2-74,

2-86

Offset Deliveries (AGM-12) F-4D . . . 1-96

Offset Deliveries (F-4E). 1-159

Offset Radar IP (F-4D). 1-76

Offset Radar IP (F-4E). 1-139

Optical Sight Camera, KB-25/A

(F-4E) . 1-160A

Optical Sight Check (F-4D). 2-27

Optical Sight Check (F-4E). 2-63

Optical Sight/Gun Firing (F-4E). . . . 1-128

Optical Sight, Lead Computing (F-4D) . 1-56

Optical Sight, Lead Computing (F-4E) . 1-118

Outboard Station Jettison (F-4C) . . . 3-5

Outboard Station Selective Jettison

(F-4C). 1-20

Outboard Station Selective Jettison

(F-4D). 1-81

Outboard Wing Station Jettison (F-4C) . 1-20

Outboard Wing Station Jettison (F-4D) . 1-81

Outboard Wing Station Jettison (F-4E) . 1-144

Parallax Error. 4-8

Parallel vs. Converged Fire. 4-8

PAU-7/A Spray Tank. 1-208

PAU-7/A Spray Tank (F-4C). 2-8

PAU-7/A Spray Tank (F-4D). 2-42

PAU-7/A Spray Tank (F-4E). 2-77

PAU-7/A Spray Tank (F-4E) After
T.O. 1F-4E-556 . 2-95

2-96

1-6A

4-1

1-40

1-104

1-170

1-169

1-170

1-171

1-173

1-205

1-191

1-205

1-224

Change 6

Index 8

T.O. 1F-4C-34-1-1

Page No.

Practice Bombs..

Pressure Altitude.

Pullup Light (F-4D).

Pullup Tone (F-4D).

Pullup Tone Cut Off Switch (F-4C). . .
Pullup Tone Cut Off Switch (F-4D). . .
Pylons, MAU-12B/A Armament

(F-4C).

Pylon/Suspension Equipment (F-4C). .

Radar Missile Jettison (F-4D) ....

Radar Scope Camera.

Radar Transponder SST-181X . . . .
Range Bar Triple Ranging (F-4D) . . .

Range Switch (F-4D).

Range Switch (F-4E).

Rate Switch (F-4E).

Rate Switch (Nose Gun) F-4E.

Reference Lines.

Rehoming MERS and TERS (F-4C). . .
Rehoming MERS and TERS (F-4D). . .
Rehoming MERS and TERS (F-4E). . .

Reject Switch (F-4E).

Relay, Bomb Button Transfer (F-4C) .

Relative Wind Vector Chart.

Release Advance Control (F-4D) . . .
Release Advance Control (F-4E) . . .
Release Altitude, Determination of
Minimum Acceptable.

Release and Jettison, Nuclear Stores

(F-4D).

Release Conditions.

Release Range Control (F-4D) . . . .
Release Range Control (F-4E) . . . .
Release Sequence, Normal (F-4C). . .

Reset Button (F-4E).

Reticle Cage (After T.O. 1F-4E-556). .
Reticle Caging (Before T.O. 1F-4E-

556).

Reticle Caging Mode (F-4D) . . . . .

Ripple Release Bombing (F-4C) . , , .
Ripple Release Bombing (F-4D) . . . .
Ripple Release Bombing (F-4E) . . . .

Ripple Release Computations.

Ripple Release, Impact Pattern for . .

RMU-8/A Reel Launcher.

RMU-8/A Tow Target System (F-4C/

D/E).

RMU-8/A Tow Target System Emer¬
gency Procedures .

RMU- 8/A Tow System.

Rocket Fuzes, 2.75-Inch.

Rocket Launch (F-4C).

Rocket Launch (F-4D).

Rocket Launch (F-4E).

Rocket Launch and Gun Firing Con¬
ditions .

Rocket Launch and Gun Firing Sample
Problem.

1-248

5-2

1-51

1-18

1-52

1-26

1-19

1-83

1- 250,

2- 99
1-265
1-59
1-80
1-143
1 - 110 ,
1-127
1-127
5-1
1-27
1-84
1-151
1-110
1-14
5-4
1-55
1-117

5-6

1-81

5-11

1-55

1-117

1-9

1-118

1-121

1-50,

1-59

1-5

1-38

1-102

5-15

5-2

1-256

2-100AR

Rocket Launch and Gun Firing

Tables.

Rocket Launcher, LAU-3/A.

Rocket Launchers, LAU-32, -59, -68 .
Rocket Launching 2.75-Inch FFAR. . ,
Rocket, TDU-ll/B Target (5-Inch

HVAR) F-4C.

Rocket Warheads, 2.75-Inch.

Rocket, 2.75-Inch Folding Fin Aircraft.

Rockets (F-4C).

Rockets (F-4D).

Rockets (F-4E).

Rockets and Dispenser /Ripple (F-4E) .
Rockets and Dispenser/Single (F-4E) .
Rockets and SUU-20 (F-4E) After

T.O. 1F-4E-556 .

Roll Reference Shift (AGM-12) F-4D. .

Roll Reference Shift (F-4E).

Rounds Counter (F-4E).

Rounds Limiter (F-4E).

Safe Escape.

Safe Separation Data.

Sample Problem, Dive Bombing and

Low Level Bombing.

Sample Problem, Loft Bombing. . . .
Sample Problem, Rocket Launch and

Gun Firing.

Scavenge System (Nose Gun) F-4E. , .
Scope Camera, Radar (F-4C/D/E). . .

Selective Jettison (F-4C).

Selective Jettison (F-4D).

Selective Jettison (F-4E).

Selective Jettison Knob (F-4E) . . . .
Side Ejection Impact Distance . . . .

Sight Depression Chart.

Sight Setting Computation.

Sine and Cosine Table.

Single Bomb Release.

Snakeye 1 GP Bomb, MK82.

Spray Tank, A/B 45Y-1 Liquid Agent .
Spray Tank, A/B 45Y-2 Dry Agent. . .
Spray Tank, A/B 45Y-4 Dry Agent . .
Spray Tanks, A/B 45Y-1, Y-2, Y-4. .
Spray Tank Dispensers (F-4E) A/B
45Y-1, -2, -4 After T.O. 1F-4E-556.
Spray Tank, PAU-7/A (F-4C).

3-25

1-255

1-205

1-5

1-36

1-100

5-18

Spray Tank, PAU-7/A (F-4D).

Spray Tank, PAU-7/A (F-4E).

Spray Tank, PAU-7/A (F-4E) After

T.O. 1F-4E-556 .

Spray Tank, TMU-28/B (F-4C) . . . .

Spray Tank, TMU-28/B (F-4D) . . . .

5-10

1-199

1-200

4-6

2-12

1-202

1-201

2-6

2-37

2-73

1-112

2-90

1-96

1-159

1-127

5-6

4-1

5-11

5-22

5-18

1- 125

2- 99,
1-250
1-19,

3- 3
1-81,
3-10
1-144,
3-18
1-146A
5-4
5-4
5-3
5-4
5-9
1-174
1-206

1- 207
1-208
1-206

2- 93
2 - 8 ,
1-208
2-42,
1-208
2-77,
1-208

2-95

2 - 8 ,

1-208

2-41,

1-208

Change 6

Index 9

T.O. 1F-4C-34-1-1

Spray Tank, TMU-28/B (F-4E) ....

Spray Tank, TMU-28/B (F-4E) After

T.O. 1F-4E-556 .

SST-181X, Radar Transponder ....
Station and Weapon Select Panel

(F-4D).

Station and Weapon Select Panel

(F-4E).

Station Select Buttons (AGM-.12) F-4D .

Station Select Buttons (F-4E).

Station Selector Buttons (F-4D) ....
Station Selector Buttons (F-4E) ....

Station Selector Knob (F-4C).

Step Switch (F-4C).

Step Switch, Intervalometer (F-4C) . .
Strike Camera System, KB-18A. . . .

Suspension Equipment (F-4C).

Suspension Equipment (F-4D).

Suspension Equipment (F-4E).

SUU-7 Dispensers. ..

SUU-13 Dispensers.

SUU-13/A Dispenser.

SUU-13A/A Dispenser.

SUU- 16/A Gun Pod.

SUU-16/A, -23/A Gun Pod (F-4C). . .
SUU- 16/A, -23/A Gun Pod (F-4D). . .
SUU-16/A, -23/A Gun Pod (F-4E), . .
SUU-16/A, -23/A Gun Pod (F-4E)

After T.O. 1F-4E-556.

SUU-20/A, A/A Bomb and Rocket

Dispensers .

SUU-20 Bomb/Rocket Dispensers

(F-4C).

SUU-20 Bomb/Rocket Dispensers

(F-4D).

SUU-20 Bomb/Rocket Dispensers

(F-4E).

SUU-21/A Bomb Dispenser.

SUU-21/A Bomb Dispenser (F-4C) , .
SUU-21/A Bomb Dispenser (F-4D) . .
SUU-21/A Bomb Dispenser (Modified)

F-4D.

SUU-21/A Bomb Dispenser (F-4E). . .
SUU-21/A Bomb Dispenser (Modified)

F-4E.

SUU-21/A Bomb Dispenser (Modified)
After T.O. 1F-4E-556 (F-4E) . . . .

SUU-23/A Gun Pod.

SUU-25A/A Flare Dispenser.

SUU-25B/X Flare Dispenser.

SUU-25C/A Flare Dispenser.

SUU-30 Dispensers.

SUU-30/B Dispenser.

SUU-30A/B Dispenser.

SUU-30B/B Dispenser.

SUU-30C/B Dispenser.

SUU-36 Dispensers.

SUU-3 8 Dispensers.

SUU-42/A Flare Dispenser.

Switch, Activate (F-4D).

Switch, Automatic Acquisition (F-4D) .
Switch, Arm Nose Tail (F-4D) ....
Switch, Guns and Stores (F-4D). , . .
Switch, Guns and Stores (F-4E). . . .

Page No.

2-76,

Switch, Guns Clear (F-4D).

1-49

1-208

Switch, Guns Clear (F-4E).

1-110

Switch, Gyro (F-4D).

Switch, Interval (F-4D).

1-80

2-94

1-49

1-265

Switch, Interval (F-4E)..

1-110

1-42

Switch, Left Main Gear Scissors
(F-4C).

1-20

1-106

Switch, Left Main Gear Scissors
(F-4D).

1-81

1-97

Switch, Nose Gun Rate (F-4E).

1-127

1-114B

Switch, Nose Gun Trigger (F-4E) . . .

1-127

1-46

Switch, Pullup Tone Cut Off (F-4D) . .

1-52

1-107

Switch, Range (F-4D).

1-80

1-11

Switch, TGT Find (F-4D).

1-80

1-10

Switch, Trigger (F-4D).

1-50

1-33

Switch, Trigger (F-4E).

System, Adaptive Control (F-4D) . . .

1-111

1-264

1-94

1-21

1-83

1-146A

1-179

Tail Fuzes.

1-237

1-186A

Target Finding Mode (F-4D).

1-77

1-186A

Target Finding Mode (F-4E).

1-140

1-186A

Target Insert Button (F-4E).

1-118

1-162

Target Practice, 20mm.

1-167

2-9

Target Range Controls (F-4D) ....

1-54

2-42

Target Range Controls (F-4E) ....

1-116

2-77

Target Rocket, TDU-ll/B (5-Inch

HVAR) F-4D.

2-46,

2-95

Target, TDU-10/B.

1-253

1-264

1-243

TDD-22A/B Tow Target.

1-255

TDU-10/B Target.

1-264

2-10

TDU-ll/B Target Rocket (5-inch

HVAR).

1-253,

2-44

2-12,

2-80

TDU-ll/B Target Rocket (5-inch

2-46

1-246

HVAR) (F-4C).

2-12,

2-11

1-253

2-44

TDU-ll/B Target Rocket (5-Inch

HVAR) (F-4D).

2-46,

2-44A

1-253

2-81

10-Degree Climb Angle.

4-9

TER, Triple Ejector Rack (F-4C). . .

1-27

2-82

TER, Triple Ejector Rack (F-4D). . .

1-84

TER, Triple Ejector Rack (F-4E). . .

1-151

2-97

TGT Find Switch (F-4D).

1-80

1-165

TGT Find Switch (F-4E).

1-143

1-191

Throttle Cage Button (F-4E).

1-121

1-194A

TMU-28/B Spray Tank.

1-208,

1-195

2-8,

1-185

2-41,

1-185

TMU-28/B Spray Tank (F-4C) ....

2-76

1-185

2-8,

1-186

1-190

1-198

1-80

1-51

1-48

1-49

1-110

TMU-28/B Spray Tank (F-4D) . . .

TMU-28/B Spray Tank (F-4E) . . .

TMU-28/B Spray Tank (F-4E) After

T.O. 1F-4E-556 .

Tow Target Operation..

Tow Target System, A/A 37U-15
Modified.

1-208

2-41,

1-208

2-76,

1-208

2-94

1-264

1-262

Index10

Change 6

T.O. 1F-4C-34-1-1

Page No.

Tow Target System, Modified A/A

37U-15 (F-4C). 2-12

Tow Target System, Modified A/A

37U-15 (F-4D). 2-46

Tow Target System, Modified A/A

37U-15 (F-4E). 2-82

Tow Target System, Modified A/A
37U-15 (F-4E) After T.O. 1F-4E-556. 2-98

Tow Target System, RMU-8/A (F-4C/

D/E) .. 2-100AR,

1-255

Tow Target, TDD-22A/B. 1-255

Tow System (RMU-8/A). 1-255,

2-100AR

Training Weapons and Equipment . . . 1-243

Trajectory Shift (F-4D). 1-62

Trajectory Shift (F-4E). 1-123

Transmitter and Control Selector

(AN/ARW-77) (F-4C). 1-30

Transmitter and Control Selector

(AN/ARW-77) (F-4D). 1-93

Transmitter and Control Selector

(AN/ARW-77) (F-4E). 1-156

Transponder, Radar SST-181X ....

Trigger Switch (F-4C). 1-50

Trigger Switch (F-4D). 1-50

Trigger Switch (F-4E). 1-111,

1-127

Trigger Switch (Nose Gun) F-4E . . . 1-127

Trigger Transfer Relay (F-4E) .... 1-111

Trigger Transfer Relay (F-4C) .... 1-151

Triple Ejector Rack (TER) F-4C . . . 1-27

Triple Ejector Rack (TER) (F-4D). . . 1-84

Triple Ejector Rack (TER) (F-4E). . . 1-151

Triple Ranging, Range Bar (F-4D) . . 1-59

20mm Ammunition. 1-167

20mm Armor Piercing Incendiary . . . 1-168

20mm High Explosive Incendiary . . . 1-168

20mm Target Practice. 1-167

2.75-Inch FFAR. 4-1

2.75-Inch Folding Fin Aircraft Rocket . 1-201

2.75-Inch Rocket Fuzes. 1-205

2.75-Inch Rocket Warheads. 1-202

Umbilical Test Set (UTS) AN/AWM-19 . 1-250

Uncoordinated Flight. 4-7

Up-Wind Aimpoint. 5-5

(UTS) AN/AWM-19, Umbilical Test
Set. 1-250

Page No.

Visual IP Fly-Over (F-4D). 1-77

Visual IP Fly-Over (F-4E). 1-140

Warhead and Fuze (AGM-12B and

-12C). 1-212

WDU-4A/A Fuze (Flechette). 1-206

WDU-4A/A Warhead (Flechette). . . . 1-205

Weapon Delivery Modes (F-4D) .... 1-61

Weapon Delivery Modes (F-4E) .... 1-123

Weapon Delivery Panel (F-4D) .... 1-42

Weapon Delivery Panel (F-4E) .... 1-143

Weapon Release/Launch Modes (F-4E). 1-113

Weapon Selector Knob (F-4C). 1-10

Weapon Selector Knob (F-4D). 1-46.

Weapon Selector Knob (F-4E). 1-106,

1-114

Weapon System, AGM-12 (F-4C) . . . 1-29

Weapon System, AGM-12 (F-4D) . . . 1-93

Weapons and Equipment, Trailing. . . 1-243

Weapons Release Computer Control

Panel (F-4D). 1-54

Weapons Release Computer Control

Panel (F-4E). 1-116

Weapons Release Computer Set (F-4D). 1-52

Weapons Release Computer Set (F-4E). 1-114G

Weapons Release Unit (AWRU), Air¬
craft (F-4E). 1-114C

Wind Correction. 5-5

Wind Correction - WRCS Modes

(F-4D/E). 5-5

Wind Values. 5-15

Wing and CL Station Jettison (F-4E). . 1-146A

Wingspan vs. Target Range. 1-167

WRCS Ballistic Data (F-4D/E) .... 5-8

WRCS BIT Check (F-4D). 2-31

WRCS BIT Check (F-4E). 2-67

WRCS Built-In-Test (BIT) F-4E. . . . 1-117

WRCS Delivery Modes (F-4D and

F-4E). 5-18

WRCS Drag Coefficients (Cd). 5-7

WRCS Freeze Button (F-4D). 1-56

WRCS Labs Delivery Mode (F-4D). . . 1-77

WRCS Operational Envelope (Dive

Toss Mode). 4-9

WRCS Reset Button (F-4D). 1-56

WRCS Target Insert Button (F-4D) . . 1-56

WRCS, Weapons Release Computer
Set (F-4D). 1-52

* U.$. GOVERNMENT PRINTING OFFICE: 1972

769-067/5274

Change 6

Index 11 / (Index 12 blank)

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